JP6991542B2 - Injection system - Google Patents

Description

Application of Article 30, Paragraph 2 of the Patent Law Toshihiro Nakajo, 3 outsiders, "Development of vapor-liquid equilibrium pressure regulation system for small satellites", 59th Space Science and Technology Association Lecture Meeting, Japan Society for Aeronautics and Astronautics The Japan Society for Aeronautics and Astronautics, October 7, 2015, 2B04

Application of Article 30, Paragraph 2 of the Patent Act October 8, 2015 Presented at the 59th Space Science and Technology Association Lecture hosted by The Japan Society for Aeronautics and Astronautics

The present invention relates to an injection system. In particular, the present invention relates to an injection system that can be used in a one-component, two-component, or three-component or more liquid fuel propulsion system using a vapor-liquid equilibrium pressure-regulating system.

As a propulsion system using liquid fuel, a one-component propulsion system and a two-component propulsion system are known. As a one-liquid propulsion system, hydrazine (N ₂ H ₄ ) is used as a liquid fuel, and this is brought into contact with an iridium-containing catalyst to generate a high-temperature injection gas to obtain thrust, and hydrogen peroxide is used as a liquid fuel. As a two-component propulsion system (blowdown method, pressure regulation method), hydrazine is used as a liquid fuel, dinitrogen tetraoxide is used as an oxidizing agent, and these are mixed and burned to generate an injection gas. A method of generating the fuel and a method of using liquid hydrogen as a fuel and liquid oxygen as an oxidizing agent are known.

In a two-component propulsion system, a pressure regulating mechanism using a high-pressure gas may be provided for high performance (pressure regulating method, see FIG. 2B described later). In this method, the pressure in both tanks is adjusted by supplying the high-pressure inert gas contained in the high-pressure gas tank to the liquid fuel tank and the oxidant tank via a regulator. However, since such a propulsion system includes a high-pressure gas system, there is a risk of gas or liquid leaking, and there is a problem that the mass of the system as a whole increases.

Further, if the pressure of the two liquids (liquid fuel, oxidant) system is adjusted by a common piping system as in the example of FIG. 2B, the two liquids may flow back to the high pressure gas tank side and be mixed. It is probable that the failure to insert the Venus orbit of the Venus probe "Akatsuki" and the explosion of the Mars probe "Mars Observer" were caused by such causes.

In this regard, the two-component propulsion system of the asteroid explorer "Hayabusa 2" prevents the two-component mixing by completely separating the two-component pressure regulation mechanism. However, such a configuration further increases the mass of the entire system and increases the risk of leakage. In addition, since the pressure of the two liquids is controlled separately, the pressure may become unbalanced and abnormal injection may occur.

Special Table No. 11-500803 Gazette Japanese Unexamined Patent Publication No. 2015-214956

Initial Galileo Propulsion System in-Flight characterization, AIAA / SAE / ASME / ASEE 29th Joint Propulsion Conference and Exhibit, AIAA93-2117, Monterey, June 28-30, 1993 Makoto Yoshikawa, "Hayabusa2" Regarding additional measures for the chemical propulsion system [online], November 22, 2011, Japan Aerospace Exploration Agency Moon and Planetary Exploration Program Group (JSPEC) Hayabusa2 Project Team, [2016 Search on January 28], Internet <URL: http://www.mext.go.jp/b_menu/shingi/uchuu/016/002/gijiroku/__icsFiles/afieldfile/2011/12/02/1313456_01.pdf> Bruce E. Poling., George H., Thomson., Daniel G. Friend., Richard L. Rowley., W. Vincent Wilding: Perry's Chemical Engineers' Handbook 8th Edition Section 2: Physical and Chemical Data, Page 2-384, 2007.

In view of the above, it is an object of the present invention to provide an injection system capable of adjusting the pressure without using a high pressure gas system.

In order to solve the above problems, in the injection system according to the present invention, a jet flow for accommodating an injection substance and a pressurizing substance and a jet flow for generating a jet flow from the injection substance accommodated in the accommodating portion. It is provided with a generation unit and an injection port for injecting a jet flow generated by the jet flow generation unit, and at least a part of the pressurizing substance is vaporized in the accommodation unit to pressurize the inside of the accommodation unit.

The injection system further includes a separating member provided in the accommodating portion, which separates the injection substance and the pressurizing substance, and transmits the pressurization by the pressurizing substance to the injection substance.

The heat capacity of the injection substance is larger than the heat capacity of the pressurizing substance.

The accommodating portion accommodates a second pressurizing substance that pressurizes the accommodating portion.

The injection system further includes a temperature control unit that controls the temperature inside the accommodation unit to vaporize the pressurizing substance.

In order to solve the above problems, the injection system according to the present invention has a first accommodating portion for accommodating a first injection substance and a first pressurizing substance, a second injection substance, and a second. Injection from the second accommodating portion accommodating the pressurizing material, the first propellant material accommodated in the first accommodating portion, and the second propellant material accommodated in the second accommodating portion. The first and second injection materials are the first and second injection materials, respectively, provided with an injection flow generation unit that generates a flow and an injection port that injects the injection flow generated by the injection flow generation unit. Pressurization is performed in the first and second accommodating portions by vaporizing at least a part of the accommodating portion.

The first injection substance is a fuel, the second injection substance is an oxidant, and the jet flow generator burns the fuel by mixing the fuel and the oxidant. Generate the jet flow.

The injection system according to the present invention is further provided in the first accommodating portion, separates the first injection substance and the first pressurizing substance, and is used as the first injection substance. The first separating member for transmitting the pressurization by the pressurizing substance 1 and the second jetting substance and the second pressurizing substance provided in the second accommodating portion are separated from each other, and the second pressurizing substance is separated. It has a second separating member for transmitting the pressurization by the second pressurizing substance to the injection substance of 2.

The heat capacity of the first injection substance is larger than the heat capacity of the first pressurizing substance, and the heat capacity of the second injection substance is larger than the heat capacity of the second pressurizing substance.

The first accommodating portion accommodates a third pressurizing substance that pressurizes the first accommodating portion, and the second accommodating portion is a fourth pressurizing substance that pressurizes the second accommodating portion. To accommodate.

The injection system according to the present invention further controls the temperature in the first accommodating portion to control the temperature in the first accommodating portion and the first temperature control unit for vaporizing the first pressurizing substance. It has a second temperature control unit that controls and vaporizes the second pressurizing substance.

In the injection system according to the present invention, as a storage unit for k, which accommodates the kth jetting substance and the kth pressurizing substance, for an integer k from 1 to n (n is an integer of 2 or more). A jet flow generating unit that generates a jet flow from the first to nth accommodating portions, the first to nth accommodating portions accommodated in the first to nth accommodating portions, respectively, and the jet flow generating unit. It is provided with an injection port for injecting a jet flow generated by a jet flow generation unit, and at least a part of the first to nth pressurizing substances is vaporized in the first to nth accommodation units. , The inside of the first to nth accommodating portions is pressurized.

According to the present invention, in the injection system, the pressure can be adjusted by vaporizing the pressurizing substance without using a separate high-pressure gas system such as a high-pressure gas tank, so that the possibility of leakage is reduced and the weight of the injection system is reduced. Is also possible.

The conceptual diagram of the one-component vapor-liquid equilibrium pressure regulation system taught by this invention. The conceptual diagram of the two-component vapor-liquid equilibrium pressure regulation system taught by the present invention. Conceptual diagram of a conventional pressure control system using a high-pressure gas system. The system diagram figure of the one-component injection system which concerns on 1st Embodiment of this invention. FIG. 3A is a system diagram showing a modified example of the one-component injection system of FIG. 3A. FIG. 3A is a system diagram showing a modified example of the one-component injection system of FIG. 3A. FIG. 3A is a system diagram showing a modified example of the one-component injection system of FIG. 3A. The system diagram figure of the two-component injection system which concerns on the 2nd Embodiment of this invention. The system diagram figure of the three-component injection system which concerns on 3rd Embodiment of this invention. Schematic diagram of the one-component injection system used for the injection test. Vapor pressure curve of alternative Freon gas HFC-218 (C ₃ F ₈ ) (cited from Non-Patent Document 3). Appearance of the fuel tank used for the injection test The graph which shows the temperature measurement result of test 1. The graph which shows the pressure measurement result of the test 1 to 3. The graph which shows the pressure measurement result of test 4. The graph which compared the pressure measurement result of the test 4 and 5.

From this, an embodiment of the injection system according to the present invention will be described with reference to the drawings. However, the injection system according to the present invention is not limited to the specific specific configuration shown by each drawing and the related description, and can be appropriately changed within the scope of the present invention. For example, the liquefied gas is used as the pressurizing substance in the following examples, but the injection of the present invention can also be performed by using a substance that sublimates from a solid to a gas as the pressurizing substance and recovering the pressure in the accommodating portion by the sublimation. The system can be implemented. Further, in the embodiment including a plurality of accommodating portions, the first, second, and subsequent pressurizing substances may be partially or all the same, or may be all different substances. Even when an additional pressurized gas is used, the gas to be used is arbitrary as long as the reactivity with the pressurizing substance is low, and when the additional pressurized gas is used in the plurality of accommodating portions in the embodiment including the plurality of accommodating portions, the additional pressurized gas is used. The first, second, and subsequent pressurized gases may be partially or wholly the same, or may be all different gases. Further, although the injection system is described as an injection system for a propulsion device in the following examples, the injection system of the present invention can be used for other purposes.

Concept of Vapor-Liquid Equilibrium Pressure Control System The present invention proposes a gas-liquid equilibrium pressure control system as a new pressure control system typically used for a propulsion system for small spacecraft. Conceptual diagrams of a one-component type and a two-component type vapor-liquid equilibrium pressure regulation system are shown in FIGS. 1 and 2A, respectively. Further, FIG. 2B shows a conceptual diagram of a conventional pressure regulating system using a high-pressure gas system.

In the gas-liquid equilibrium pressure control system, a liquefied gas is used as a "pushing gas" for pressing the (liquid) fuel or the (liquid) oxidant (in the case of a two-component type) contained in the tank. The inside of the tank is partitioned by a pressure-deformable diaphragm, and pressure is transmitted via the diaphragm between the region on the liquefied gas side and the region on the fuel or oxidizer side.

Even if the pressure inside the tank temporarily drops due to the release of fuel and oxidizing agent from the tank due to the thrust generation operation, the pressure inside the tank will be the same as that of the liquefied gas due to the evaporation of the liquefied gas in the liquid state. The pressure is adjusted to the vapor pressure. That is, regardless of the remaining amount of fuel and oxidant, the inside of the tank is maintained in a gas-liquid equilibrium state, and the pressure becomes constant with the saturated vapor pressure of the liquefied gas (when the pressure drop is large or when continuous injection is performed). Even so, the pressure will recover, at least in part.) As a result, fuel and oxidizer can be stably supplied to the reaction chamber (combustion chamber) of the propeller.

Compared with the conventional pressure control system using a high pressure gas tank, the gas-liquid equilibrium pressure control system is advantageous in the following points.
1. 1. Since no high pressure gas tank and regulator are used, the entire system is lightweight.
2. 2. Since there is no high-pressure gas system (the vapor pressure of the liquefied gas is the maximum pressure in the entire system), the possibility of leakage can be reduced.
3. 3. (In the case of the two-component type) Since the fuel tank and the oxidizer tank are not directly connected, there is no risk that the fuel and the oxidizer will be mixed in an unexpected place (in the piping upstream of the tank, etc.).
4. (In the case of the two-component type) The mixing ratio O / F of the fuel and the oxidant can be controlled by controlling the temperature of the liquefied gas.

It is also possible to configure a gas-liquid equilibrium pressure regulation system as a hybrid system by reducing the filling amount of the liquefied gas in the tank and adding an additional pushing gas such as nitrogen gas instead. FIG. 1 shows a configuration in which nitrogen gas N ₂ is added to a one-component vapor-liquid equilibrium pressure regulation system, but an additional push gas can be similarly added even in the case of a two-component system or more. In this case, the pressure in the tank is not constant, but the system can be further reduced in weight and the total pressure in the tank can be increased. Furthermore, it is possible to estimate the remaining amount of fuel or oxidizer from the measured pressure in the tank.

Configuration diagram 3A of the injection system shows a system diagram of a one-component injection system 1 (propellant) that can be used in a propulsion system for a small spacecraft according to the first embodiment of the present invention. The injection system 1 includes a storage container 2, an injection / discharge valve 9A, a filter 10, a latch solenoid valve 11, a test port 9D-1, a pressure sensor 15A, and a propellant valve 12A-1, 12A-2. A reaction chamber 13 and an injection port 14 are provided.

The configurations of various valves, filters, piping systems, etc. are substantially the same as those described in FIG. 1 and the like of Japanese Patent Application Laid-Open No. 2015-214956. That is, the liquid fuel is injected into or discharged from the storage container 2 by the injection / discharge valve 9A, impurities in the liquid fuel released from the storage container 2 are removed by the filter 10, and the latch type electromagnetic valve 11 By opening and closing the propellant valves 12A-1 and 12A-2, the passage of the liquid fuel from which impurities have been removed to the reaction chamber 13 side is controlled.

The accommodating container 2 in the present embodiment corresponds to the accommodating portion, the latch type solenoid valve 11 and the propellant valves 12A-1 and 12A-2 correspond to the jet substance supply unit, and the reaction chamber 13 corresponds to the jet flow generation. Corresponds to the department.

In the reaction chamber 13, a catalyst (when hydrazine is used as the liquid fuel, an iridium-containing catalyst or the like) acts on the liquid fuel to generate an injection gas, and the injection gas is injected from the injection port 14 to generate thrust.

The storage container 2 is made of SUS (stainless steel) or the like as in Patent Document 2. The inside of the storage container 2 is partitioned by a diaphragm 3 which is a separating member made of a pressure-deformable material such as rubber, and a liquid fuel 4 such as hydrazine (N ₂ H ₄ ) which is an injection substance is in one region. Is housed, and a liquefied gas such as an alternative CFC-218 (C ₃ F ₈ ), which is a pressurizing substance, is housed in the other region. The liquefied gas 6 in the liquid state and the liquefied gas 7 in the gaseous state are stored in the region on the liquefied gas side of the storage container 2, but these may be mixed and stored as shown in FIG. 3A. Alternatively, as shown as a modification in FIG. 3B, the liquefied gas 6 in a liquid state may be held by the foamed metal 5 that functions as a pressurizing substance holding portion that holds the pressurizing substance. In the configuration of FIG. 3B, for example, a foamed metal 5 made of copper, SUS, etc. having a porosity of about 95% is attached to the inner wall of the liquefied gas side region of the storage container 2 by using an adhesive, as in Patent Document 2. The liquefied gas 6 in a liquid state is held by the surface tension of the gas-liquid interface formed between the pores of the foamed metal 5 (Patent Document 2, [0004], and Patent Document 1). The gaseous liquefied gas 7 is housed in the space region on the liquefied gas side as shown in FIG. 3B.

In the region on the liquefied gas side, the vapor pressure of the liquefied gas 7 in the gaseous state is dominant rather than the gravity applied to the liquefied gas 6 in the liquid state, and it is not essential to hold the liquefied gas 6 in the liquid state by the foamed metal 5. However, it is considered that holding the injection system 1 stabilizes the attitude control and causes heat conduction from the heater 8 to the liquefied gas promptly. On the other hand, since the weight of the injection system 1 is increased by using the foamed metal 5, it is preferable to use the configuration shown in FIG. 3A in order to reduce the weight of the system. The injection system of the present invention can be implemented in either a configuration using or not using foamed metal (in the modified examples shown in FIGS. 4 and 4 and in the two-component, three-component or higher injection systems shown in FIGS. 6 and later). The same applies).

Further, on the outer wall of the storage container 2, a heater 8 that controls the temperature inside the storage container 2 so that the liquefied gas 6 in a liquid state vaporizes based on the temperature inside the storage container 2 detected by a temperature sensor (not shown) is provided. It is installed all around.

In FIGS. 3A and 3B, the line segment connecting each component represents a pipe as in Patent Document 2. The pressure sensor 15A and the test port 9D-1 are the same as those included in the configuration of Patent Document 2, and the pressure in the pipe is monitored by the pressure sensor 15A and the propeller valves 12A-1 and 12A-2 are closed. In this state, open the test port 9D-1 and inject helium gas or the like to check for leaks.

Operation of the injection system The operation of the injection system 1 will be described below. Here, as in Patent Document 2, the opening / closing of each solenoid valve and the operation control of the heater, various sensors, etc. are performed by remote control or the like via an arbitrary control circuit (not shown), and each injection / exhaust valve is used. Liquid injection (injection) and drainage (exhaust) from the air are typically performed by the operator, but the specific means for controlling and operating these can be appropriately changed according to the embodiment. be. It is assumed that the liquefied gas 6 (liquid) and 7 (gas) are stored in advance in the liquefied gas side region in the storage container 2 (the injection / discharge valve for injecting the liquefied gas, etc.). Not shown).

In preparation for the operation of the injection system 1, first, the liquid fuel 4 is injected from the injection / discharge valve 9A into the liquid fuel side region of the storage container 2. The liquefied gas side region of the storage container 2 is in a gas-liquid equilibrium state of the liquefied gas, and the diaphragm 3 is pressed by the vapor pressure of the liquefied gas. When the diaphragm 3 is deformed by the pressure, the pressure is also applied to the liquid fuel 4. When the latch type solenoid valve 11 is opened and the propellant valves 12A-1 and 12A-2 are further opened in this state, the liquid fuel 4 released from the storage container 2 by the vapor pressure of the liquefied gas and whose impurities have been removed by the filter 10 is released. It is supplied to the reaction chamber 13, and the liquid fuel 4 is acted on by the catalyst in the reaction chamber 13 to generate an injection gas. Thrust is generated by injecting the injection gas from the injection port 14.

The pressure inside the storage container 2 temporarily decreases due to the release of the liquid fuel 4 from the storage container 2, but the pressure recovers when the liquefied gas 6 in the liquid state evaporates. If there is a sufficient time interval before the next injection operation, the liquid liquefied gas 6 and the gaseous liquefied gas 7 in the liquefied gas side region in the storage container 2 return to the gas-liquid equilibrium state, and the pressure is also liquefied gas. It recovers to the vapor pressure of.

Further, when the liquefied gas 7 in a gaseous state expands due to the injection operation and the temperature inside the storage container 2 drops, the vapor pressure of many liquefied gases also drops, so that the pressure drops even inside the storage container 2. In this case, the storage container 2 can be heated by the heater 8 to recover the temperature and pressure in the storage container 2. However, the pressure drop may not be large when the heat capacity of the liquid fuel 4 is larger than the heat capacity of the liquefied gases 6 and 7, and heat flows from the liquid fuel 4 to the liquefied gases 6 and 7 to maintain the temperature. be. It is not essential to use the heater 8 in the injection system 1 of this embodiment.

If the vapor pressure of the liquefied gas is controlled by controlling the heater 8 to arbitrarily change the temperature inside the storage container 2, the pressure applied to the liquid fuel 4 via the diaphragm 3 is controlled, and the liquid fuel 4 is controlled. It is also possible to adjust the supply amount (supply rate) of. Further, as already described, if an additional push gas such as nitrogen gas is accommodated in the region on the liquefied gas side in the accommodation container 2, the pressure in the accommodation container 2 is increased and the supply amount of the liquid fuel 4 is increased. be able to.

The internal configuration of the modified storage container 2 is not limited to that shown in FIGS. 3A and 3B, and can be arbitrarily changed to the extent that the present invention can be carried out. As an example, by using a bag-shaped bladder 16 made of a pressure-deformable material such as rubber instead of the diaphragm 3, the inside of the storage container 2 may be separated into a region on the liquid fuel side and a region on the liquefied gas side (Fig.). 4). When the bladder 16 is pressed and deformed by the vapor pressure of the liquefied gas 7, the liquid fuel 4 is discharged from the storage container 2. After that, the injection operation can be performed in the same operation as that of FIGS. 3A and 3B.

Alternatively, the injection system 1 may be configured without using a separating member such as the diaphragm 3 or the bladder 16 (FIG. 5). In this case, the liquid fuel 4 and the liquefied gas 6 in the liquid state are mixed in the storage container 2, and these are pressed by the liquefied gas 7 in the gaseous state and discharged from the storage container 2. The released liquid fuel 4 and the liquefied gas 6 in a liquid state are sent to the reaction chamber 13 in the same manner as in the configurations of FIGS. 3A and 3B, and the liquid fuel 4 is acted on by a catalyst to generate an injection gas. .. Thrust is generated by injecting the injection gas and the liquefied gas from the injection port.

Configuration of the injection system FIG. 6 shows a system diagram of the two-component injection system 1 according to the second embodiment of the present invention. The two-component injection system 1 includes a storage container 2, an injection / discharge valve 9A, a filter 10, a latch solenoid valve 11, a test port 9D-1, a pressure sensor 15A, and a propellant valve in the one-component injection system 1 of FIG. 3A. It has two sets of configurations up to 12A-1 and 12A-2, and thereafter has the same configuration as the one-component system 1. However, in this embodiment, in order to explain an embodiment in which the injection gas is generated by combustion of the liquid fuel and the oxidant, a combustion reaction is performed instead of a catalytic reaction in the reaction chamber 13. In the configuration of FIG. 6, the same elements as those of the configuration of FIG. 3A are represented by the same reference numerals, and description thereof will be omitted as appropriate.

In the injection system 1 of FIG. 6, the storage container 2A is separated into a region on the liquid fuel side and a region on the liquefied gas side by the diaphragm 3A, and the liquid fuel 4 such as hydrazine is on the liquefied gas side in the region on the liquid fuel side. A liquefied gas such as HFC-218 is contained in the region. In the system configuration of FIG. 6, the liquefied gas 6A in the liquid state and the liquefied gas 7A in the gaseous state are not particularly separated, but the liquefied gas 6A in the liquid state is held by the foam metal as in the configuration of FIG. 3B. , The gaseous liquefied gas 7A may be accommodated in the space region on the liquefied gas side. The structure of the storage container 2B is the same as that of the storage container 2A, but one of the regions separated by the diaphragm 3B contains an oxidizing agent 17 such as dinitrogen tetroxide instead of the liquid fuel 4. The area on the liquefied gas side is the same as that of the storage container 2A. The diaphragm 3A is preferably made of rubber or the like, whereas the diaphragm 3B is preferably made of a metal or the like having low chemical reactivity with the oxidizing agent 17.

Operation of the injection system The liquefied gas side region in the storage container 2A contains the liquefied gas 6A (liquid) and 7A (gas) in advance as in the first embodiment, and the liquefied gas side region in the storage container 2B contains the liquefied gas 6A (liquid) and 7A (gas). Similarly, it is assumed that the liquefied gas 6B (liquid) and 7B (gas) are contained (the injection / discharge valve for injecting the liquefied gas, etc. is not shown). To prepare for the operation of the injection system 1, first, the liquid fuel 4 is injected from the injection / discharge valve 9A into the liquid fuel side region of the storage container 2A, and then the oxidant 17 is injected from the injection / discharge valve 9B into the oxidant side region of the storage container 2B. .. The liquefied gas side regions of the containing containers 2A and 2B are in a gas-liquid equilibrium state of the liquefied gas, respectively, and the diaphragms 3A and 3B are pressed by the vapor pressure of the liquefied gas, respectively. When the diaphragms 3A and 3B are deformed by the pressure, pressure is also applied to the liquid fuel 4 and the oxidant 17. In this state, the latch type electromagnetic valves 11A and 11B are opened, and further the propelling valves 12A-1 and 12A-2 and the propelling valves 12B-1 and 12B-2 are opened. The liquid fuel 4 and the oxidant 17, which are discharged from 2B and whose impurities are removed by the filters 10A and 10B, respectively, are supplied to the reaction chamber 13, and the liquid fuel 4 and the oxidant 17 are mixed and burned in the reaction chamber 13. As a result, injection gas is generated. Thrust is generated by injecting the injection gas from the injection port 14.

The liquid fuel 4 is released from the storage container 2A, and the oxidizing agent 17 is released from the storage container 2B, so that the pressure in the storage containers 2A and 2B temporarily decreases, but the liquefied gases 6A and 6B in the liquid state are used, respectively. The pressure is restored by evaporating. If there is a sufficient time interval before the next injection operation, the liquefied gas side region in the containing containers 2A and 2B returns to the gas-liquid equilibrium state, and the pressure also recovers to the vapor pressure of the liquefied gas.

Further, when the liquefied gases 7A and 7B in a gaseous state expand due to the injection operation and the temperature in the storage containers 2A and 2B drops, the vapor pressure also drops in many liquefied gases, so that the pressure drops even in the storage containers 2A and 2B. Occur. In this case, the storage containers 2A and 2B can be heated by the heaters 8A and 8B, respectively, to recover the temperature and pressure in the storage containers 2A and 2B, respectively. However, the heat capacity of the liquid fuel 4 and the oxidant 17 is larger than the heat capacity of the liquefied gases 6A, 7A, 6B, and 7B, and the liquid fuel 4 becomes the liquefied gas 6A, 7A, and the oxidant 17 becomes the liquefied gas 6B, 7B. The pressure drop may not be large, such as when heat flows in and the temperature is maintained. It is not essential to use the heaters 8A and 8B in the injection system 1 of this embodiment.

If the vapor pressure of the liquefied gas is controlled by controlling the heaters 8A and 8B to arbitrarily change the temperatures in the storage containers 2A and 2B, the pressure applied to the liquid fuel 4 via the diaphragm 3A and the diaphragm 3B It is also possible to control the pressure applied to the oxidant 17 via the liquid fuel 4 and adjust the supply amount (supply rate) of the liquid fuel 4 and the oxidant 17. The heater 8A and the heater 8B can be controlled independently, and if the supply amounts of the liquid fuel 4 and the oxidant 17 are independently controlled by controlling the temperatures of the storage containers 2A and 2B independently, the liquid fuel 4 and the oxidizer can be oxidized. The mixing ratio O / F with the agent 17 can be arbitrarily controlled. Further, as already described, if an additional push gas that functions as a second pressurizing substance such as nitrogen gas is contained in one or both of the storage containers 2A and 2B, and in the region on the liquefied gas side, the container is stored. The internal pressure of one or both of the containers 2A and 2B can be increased to increase the supply of one or both of the liquid fuel 4 and the oxidizing agent 17. In one or both of the storage containers 2A and 2B of the two-component injection system 1, a bladder is used instead of the diaphragm as in the configuration of FIG. 4, or the inside of the storage container is 2 as in the configuration of FIG. It is possible to configure the injection system 1 as a modified example in which the fuel or the oxidant is configured to be mixed with the liquefied gas without being separated into two regions.

Configuration of the injection system FIG. 7 shows a system diagram of the three-component injection system 1 according to the third embodiment of the present invention. The three-component injection system 1 includes a storage container 2, an injection / discharge valve 9A, a filter 10, a latch solenoid valve 11, a test port 9D-1, a pressure sensor 15A, and a propellant valve in the one-component injection system 1 of FIG. 3A. It has three sets of configurations up to 12A-1 and 12A-2, and thereafter has the same configuration as the one-component system 1. However, in this embodiment, in order to explain an embodiment in which an injection gas is generated by burning three types of liquid fuel as an example, a combustion reaction with three types of liquid fuel is performed in the reaction chamber 13. As another example, the three-component injection system 1 can be configured by accommodating different types of liquid fuels in two accommodating containers and accommodating an oxidant in one accommodating container. In the configuration of FIG. 7, the same elements as those of the configuration of FIG. 3 are represented by the same reference numerals, and description thereof will be omitted as appropriate.

In the injection system 1 of FIG. 7, the storage container 2A is separated into a region on the liquid fuel side and a region on the liquefied gas side by the diaphragm 3A, and the liquid fuel 4 is in the region on the liquid fuel side in the region on the liquefied gas side. Contains a liquefied gas such as HFC-218. In the system configuration of FIG. 7, the liquefied gas 6A in the liquid state and the liquefied gas 7A in the gaseous state are not particularly separated, but the liquefied gas 6A in the liquid state is held by the foam metal as in the configuration of FIG. 3B. , The gaseous liquefied gas 7A may be accommodated in the space region on the liquefied gas side. The configurations of the storage containers 2B and 2C are the same as those of the storage containers 2A, but different types of liquid fuels 18 and 19 are stored in one of the regions separated by the diaphragms 3B and 3C. The area on the liquefied gas side is the same as that of the storage container 2A.

Operation of the injection system The liquefied gas 6A (liquid) and 7A (gas) are previously stored in the liquefied gas side region in the storage container 2A as in the first embodiment, and are stored in the liquefied gas side region in the storage container 2B. Similarly, the liquefied gas 6B (liquid) and 7B (gas) are contained, and the liquefied gas 6C (liquid) and 7C (gas) are also contained in the liquefied gas side region in the storage container 2C. (The injection / exhaust valve for injecting liquefied gas, etc. is not shown). To prepare for the operation of the injection system 1, first, the liquid fuels 4, 18 and 19 are injected from the injection / discharge valves 9A, 9B and 9C into the liquid fuel side regions of the storage containers 2A, 2B and 2C. The liquefied gas side regions of the containing containers 2A, 2B, and 2C are in a gas-liquid equilibrium state of the liquefied gas, respectively, and the diaphragms 3A, 3B, and 3C are pressed by the vapor pressure of the liquefied gas, respectively. When the diaphragms 3A, 3B, and 3C are deformed by the pressure, pressure is also applied to the liquid fuels 4, 18 and 19. In this state, the latch type electromagnetic valves 11A, 11B, 11C are opened, and the propellant valves 12A-1, 12A-2, the propellant valves 12B-1, 12B-2, and the propellant valves 12C-1, 12C-2 are further opened. When opened, the liquid fuels 4, 18 and 19, which are discharged from the storage containers 2A, 2B and 2C by the vapor pressure of the liquefied gas and whose impurities are removed by the filters 10A, 10B and 10C, respectively, are supplied to the reaction chamber 13 for reaction. Injected gas is generated by mixing and burning the liquid fuels 4, 18 and 19 in the chamber 13. Thrust is generated by injecting the injection gas from the injection port 14.

When the liquid fuels 4, 18 and 19 are released from the storage containers 2A, 2B and 2C, the pressure in the storage containers 2A, 2B and 2C temporarily decreases, but the liquid gas 6A, 6B and 6C are released. The pressure is restored by evaporating each. If there is a sufficient time interval before the next injection operation, the liquefied gas side region in the containing containers 2A, 2B, and 2C returns to the vapor-liquid equilibrium state, and the pressure also recovers to the vapor pressure of the liquefied gas.

Further, when the liquefied gas 7A, 7B, 7C in a gaseous state expands due to the injection operation and the temperature in the storage container 2A, 2B, 2C drops, the vapor pressure also drops in many liquefied gas, so that the storage container 2A, 2B, The pressure drops even within 2C. In this case, the storage containers 2A, 2B, and 2C can be heated by the heaters 8A, 8B, and 8C, respectively, to recover the temperature and pressure in the storage containers 2A, 2B, and 2C. However, the heat capacities of the liquid fuels 4, 18 and 19 are larger than the heat capacities of the liquefied gases 6A, 7A, 6B, 7B, 6C and 7C, and the liquid fuel 4 is changed to the liquefied gases 6A and 7A, and the liquid fuel 18 is changed to the liquefied gas 6B. , 7B, and when heat flows from the liquid fuel 19 to the liquefied gases 6C and 7C to maintain the temperature, the pressure drop may not be large. It is not essential to use the heaters 8A, 8B, 8C in the injection system 1 of this embodiment.

If the vapor pressure of the liquefied gas is controlled by controlling the heaters 8A, 8B, 8C and arbitrarily changing the temperature in the storage containers 2A, 2B, 2C, the liquid fuel is supplied via the diaphragms 3A, 3B, 3C. It is also possible to adjust the supply amount (supply rate) of the liquid fuels 4, 18 and 19 by controlling the pressure applied to the 4, 18 and 19. The heaters 8A, 8B and 8C can be controlled independently, and if the supply amounts of the liquid fuels 4, 18 and 19 are independently controlled by controlling the temperatures of the storage containers 2A, 2B and 2C independently, the liquid fuel 4, The mixing ratio of 18 and 19 can be arbitrarily controlled. Further, as already described, if an additional push gas such as nitrogen gas is accommodated in one or more of the storage containers 2A, 2B, 2C, and in the region on the liquefied gas side, one of the storage containers 2A, 2B, 2C is used. The above internal pressure can be increased to increase the supply amount of one or more of the liquid fuels 4, 18 and 19. In addition, even in one or more of the storage containers 2A, 2B, and 2C of the three-component injection system 1, a bladder is used instead of the diaphragm as in the configuration of FIG. 4, or in the storage container as in the configuration of FIG. It is possible to configure the injection system 1 as a modified example in which the fuel is not separated into two regions and the fuel is mixed with the liquefied gas. A four-component or higher injection system can be configured on the same principle.

Injection test As an example of the injection system according to the present invention, a one-component injection system was constructed and an injection test was conducted.

Configuration Figure 8 shows a schematic diagram of the one-component injection system used in the injection test. The inside of a spherical tank with a diameter of 400 mm and a volume of 38 L designed for a small satellite is separated by a diaphragm, and HFC-218 (vapor pressure curve is shown in FIG. 9) which is a push gas in one region. Refer to 3. The filling amount is 2.5 kg or 1.0 kg. See Table 1.), And the other region contains water as a dummy fuel. MLI (Multi Layer Insulation: Multilayer insulation, generally the most) to prevent the HFC-218 from expanding due to external heat transfer and affecting the measurement results and to simulate the actual satellite-mounted configuration. It is manufactured by using an aluminum-deposited polyimide for the outer layer, an aluminum-deposited mylar film for the inner layer, and a polyester net to prevent contact between the layers.) Wrap the fuel tank in a vacuum chamber and insulate the tank from the outside. (Fig. 10).

As shown in Table 1, the injection test was performed 5 times while changing the conditions, and the pressure on the HFC-218 side (basically equal to the pressure on the fuel side), the tank surface temperature on the HFC-218 side, and the tank surface temperature on the dummy fuel side. , And the fuel flow rate was measured. The initial flow rate at the start of injection (Table 1) was set by adjusting the needle valve on the fuel side. Assuming a thruster with a flow rate of 1 g / s (= 60 mL / min), tests 1 to 3 correspond to the case where four, two, or eight thrusters are simultaneously injected. In Tests 1 to 3, 2.5 kg of HFC-218 was filled, whereas in Test 4, the filling amount was reduced to 1.0 kg. This setting corresponds to a setting in which the filling amount of HFC-218 is reduced in order to reduce the weight of the system in the monopropellant propulsion system, and the HFC-218 liquid phase is depleted (all vaporized) in the latter half of the injection. Although the HFC-218 filling amount was 1.0 kg in Test 5, an injection system was constructed as a hybrid gas-liquid equilibrium pressure regulating system by adding nitrogen gas as an additional pushing gas at a partial pressure of 0.33 MPa. In all of Tests 1 to 5, the filling amount of the dummy fuel was unified to about 25 kg, and continuous injection was performed after setting the initial flow rate. Moreover, the temperature is not controlled by the heater.

Test Results and Discussion The temperature measurement results of Test 1 are shown in FIG. The tank surface temperature slightly decreases with injection on both the HFC-218 side and the fuel side, but the temperature decrease is 1 ° C. or less even after continuous injection of 8 kg. As described above, the tank is adiabatically insulated from the outside, but the magnitude of the temperature drop shown in FIG. 11 is significantly smaller than when it is assumed that the HFC-218 is adiabatically expanded. It is considered that this is because heat flowed from the dummy fuel having a large heat capacity to HFC-218 through the diaphragm with the expansion of HFC-218. In Tests 2 and 3, the decrease in tank temperature due to injection was extremely small, and it was found that HFC-218 can be regarded as almost isothermal expansion in continuous injection in a configuration filled with a sufficient amount of HFC-218.

Next, the pressure measurement results of Tests 1 to 3 are shown in FIG. In FIG. 12, the curve of isothermal expansion (Boyle's law, PV = constant.) Of the ideal gas according to the initial pressure of the tank is also entered. If the HFC-218 always maintains a vapor-liquid equilibrium state, the pressure should be almost constant, but in reality, the pressure drops because the evaporation of the liquid phase cannot keep up. The larger the initial flow rate, the larger the pressure drop. However, in each case, the pressure drop was very small compared to the isothermal expansion curve, and it was shown that the injection can be performed while maintaining the pressure in the tank.

Next, the pressure measurement result of Test 4 is shown in FIG. In FIG. 13, the curve of isothermal expansion (Boyle's law, PV = constant) according to the final pressure of the tank is also written. As shown in FIG. 13, the gradient of the pressure drop of HFC-218 is large at the point where the fuel injection amount is around 10 kg. From this point onward, the pressure curve of Test 4 approaches the isothermal expansion curve, and it is considered that the liquid phase of HFC-218 was depleted (all vaporized) at the time corresponding to this point. Further, even before the liquid phase is depleted, the gradient of the pressure drop in Test 4 is clearly larger than that in Tests 1 to 3. It is considered that this is because the amount of HFC-218 filled in Test 4 was smaller than that in Tests 1 to 3 and the surface area of the liquid phase was also small, so that the evaporation rate was slowed down.

Finally, the pressure measurement result of Test 5 is shown in FIG. 14 together with the result of Test 4. In test 5, since nitrogen is sealed in the tank, the pressure at the start of injection is also higher than that in test 4 by the partial pressure of nitrogen. Further, in Test 5, although the filling amount of HFC-218 is the same as that in Test 4, the liquid phase depletion point as seen in the pressure change in Test 4 is not observed. It is considered that this is because the evaporation of HFC-218 was suppressed by increasing the total pressure in the tank due to nitrogen.

The outline of the present embodiment can be described as follows, for example.

In order to solve the above problems, the present invention presents a jet flow from an accommodating portion that accommodates the injection substance and the pressurizing substance so that pressure can be transmitted, and an injection substance that is pressurized by the pressurizing substance and released from the accommodating portion. The injection material is provided with an injection flow generation unit for generating the injection flow, an injection material supply unit for supplying the injection material discharged from the accommodating unit to the injection flow generation unit, and an injection port for injecting the injection flow. Provided is an injection system configured to inject an injection flow while recovering at least a part of the pressure in the accommodating part, which is lowered by the release of the material, by vaporizing at least a part of the pressurizing substance in the accommodating part. (First injection system).

Even if the pressure inside the accommodation section drops as the injection substance such as liquid fuel or oxidant is released from the accommodation section such as the fuel tank or oxidant tank by the first injection system, the tank is further accommodated. Since the pressure in the accommodating portion can be recovered by vaporizing the pressurized substance such as the liquefied gas, the pressure can be adjusted without using the high pressure gas system. In pulse injection such as when controlling the attitude of a spacecraft, at least a part of the liquefied gas evaporates during the time from one injection to the next, so that the pressure inside the housing is completely reduced (the liquefied gas corresponding to the temperature inside the tank). It is possible to recover (up to the vapor pressure of) (recovery is partial if all the liquefied gas evaporates before the vapor pressure is reached), and in the case of continuous injection such as during orbit control. Even if there is, the pressure in the accommodating portion is recovered at least partially by the evaporation of the liquefied gas in parallel with the injection.

In the first injection system, the accommodating portion is separated into a region on the injection substance side and a region on the pressurizing substance side by a separating member provided in the accommodating portion, and the injecting substance side is separated through the separating member. The pressure can be configured to be transmitted between the region of the pressure material and the region of the pressurizing substance side. As the separating member, a diaphragm made of deformable rubber, metal, or the like, a bladder, or the like can be used.

The first injection system can be configured so that the heat capacity of the injection substance is larger than the heat capacity of the pressurizing substance. When the injection substance and the pressurizing substance are selected in this way, heat flows from the injection substance to the pressurizing substance in the accommodating portion at the time of injection, so that the temperature of the pressurizing substance is lowered and the gas state is added. It is possible to suppress the pressure drop of the pressure substance.

In the first injection system, a pressurized gas different from the pressurized substance can be further accommodated in the region on the pressurizing substance side of the accommodating portion. Additional pressurized gas can be used to increase the total pressure in the pressurizing material side region within the containment, i.e. reduce the amount of pressurizing material to be used to obtain the desired total pressure.

The first injection system may further include a temperature control unit that controls the temperature inside the accommodating unit. By controlling the temperature, it is possible to control the vapor pressure of the pressurizing substance in the accommodating portion, thereby controlling the amount of the injection substance released from the accommodating portion.

Further, in the present invention, the first accommodating portion for accommodating the first injection substance and the first pressurizing substance in a pressure transferable manner, and the second injection substance and the second pressurizing substance are pressure-transmitted. Pressurized by a second accommodating portion that can be accommodated, a first injection substance that is pressurized by the first pressurizing substance and released from the first accommodating portion, and a second pressurizing substance. A second injection substance discharged from the second accommodating portion, a jet flow generation unit that generates an injection flow from the second accommodating portion, a first injection substance released from the first accommodating portion, and a second. It is provided with an injection material supply unit for supplying the second injection substance discharged from the accommodation unit 2 to the injection flow generation unit, and an injection port for injecting the injection flow, and the first and second injections are provided. By vaporizing at least a part of each of the first and second pressurizing substances in the first and second accommodating parts, the pressure in the first and second accommodating parts, which decreased with the release of the material, respectively. Provided is an injection system configured to inject an injection flow while at least partially recovering (second injection system). Similar to the first injection system, the second injection system can inject the jet flow while recovering the pressure in the first and second accommodating portions by vaporizing the first and second pressurizing substances.

In the example of the second injection system, the first injection substance is a fuel, the second injection substance is an oxidant, and the jet flow generator is a fuel by mixing the fuel and the oxidant. Can be configured to burn to generate a jet stream. However, even if it is not such a method, the second injection system can be used by a method of generating a jet flow from any two injection substances by an arbitrary method (including a method developed in the future). It is configurable.

Also in the second injection system, the first accommodating portion has a region on the first injection substance side and a region on the first pressurizing substance side due to the first separating member provided in the first accommodating portion. The pressure is transmitted between the region on the side of the first injection substance and the region on the side of the first pressurizing substance via the first separation member, and the second accommodation is performed. The second accommodating portion is separated into a region on the second injection substance side and a region on the second pressurizing substance side by a second separating member provided in the portion, and the second accommodating portion is separated through the second separating member. , The pressure can be configured to be transmitted between the region on the side of the second injection substance and the region on the side of the second pressurizing substance.

Also in the second injection system, the heat capacity of the first injection substance is larger than the heat capacity of the first pressurizing substance, and the heat capacity of the second injection substance is larger than the heat capacity of the second pressurizing substance. Can be configured to be.

Also in the second injection system, a first pressurized gas different from the first pressurizing substance is further accommodated in the region on the first pressurizing substance side of the first accommodating portion, and the second accommodating portion is provided. A second pressurizing gas different from the second pressurizing substance can be further accommodated in the region on the side of the second pressurizing substance of the part.

The second injection system may also further include a first temperature control unit that controls the temperature inside the first accommodation unit and a second temperature control unit that controls the temperature inside the second accommodation unit. ..

Further, the present invention relates to an integer k from 1 to n (n is an integer of 2 or more) as a storage portion of k for accommodating the kth injection substance and the kth pressurizing substance so as to be pressure transferable. For the first to nth injections, which are pressurized by the first to nth accommodating portions and the first to nth pressurizing substances, respectively, and released from the first to nth accommodating portions, respectively. Supply of injection material to supply the injection flow generation unit, which generates the injection flow from the material, and the first to nth injection materials discharged from the first to nth accommodation units, respectively, to the injection flow generation unit. A unit and an injection port for injecting an injection flow are provided, and the respective pressures in the first to nth accommodating portions, which are lowered by the discharge of the first to nth injection substances, are applied to the first to nth units. Provided is an injection system configured to inject an injection flow while at least partially recovering by vaporizing at least a part of the pressure material in the first to nth accommodating portions (third injection system). ).

The injection system of the present invention can be used as any injection system for injecting a jet flow, including a propulsion system for small spacecraft.

1 Injection system 2,2A, 2B, 2C Storage container 3, 3A, 3B, 3C Diaphragm 4,18,19 Liquid fuel 5 Foam metal 6,6A, 6B, 6C Liquefied gas (liquid)
7,7A, 7B, 7C Liquefied gas (gas)
8,8A, 8B, 8C Heaters 9A, 9B, 9C, Injection / exhaust valves 9D-1 to 9D-3 Test ports 10, 10A, 10B, 10C Filters 11, 11A, 11B, 11C Latch type solenoid valves 12A-1 to 12C -2 Propulsion valve 13 Reaction chamber 14 Injection port 15A to 15C Pressure sensor 16 Bladder 17 Oxidizing agent

Claims (12)

A storage unit in which a substance for injection and a substance for pressurization in a liquid state and a gas state are stored in advance, and
A jet flow generation unit that generates a jet flow from the injection substance housed in the storage unit, and a jet flow generation unit.
An injection port that injects the jet flow generated by the jet flow generation unit, and
Equipped with
The injection substance and the pressurizing substance in a liquid state are mixed, and the substance is mixed.
By vaporizing at least a part of the pressurizing substance in the liquid state in the accommodating portion, the mixed injection substance and the pressurizing substance in the liquid state are pressed by the pressurizing substance in the gaseous state. An injection system emitted from the accommodating section. The injection system according to claim 1, wherein the heat capacity of the injection substance is larger than the heat capacity of the pressurizing substance. The injection system according to claim 1, wherein the accommodating portion accommodates a pressurizing substance different from the pressurizing substance, which presses the mixed injection substance and the pressurizing substance in a liquid state. The injection system according to claim 1, further comprising a temperature control unit that controls the temperature inside the storage unit to vaporize the pressurizing substance in a liquid state. The injection system according to claim 4, wherein the temperature control unit includes a heater mounted over the entire circumference of the accommodation unit. A first accommodating portion in which a first injection substance and a first pressurizing substance in a liquid state and a gaseous state are pre-accommodated, and
A second accommodating portion in which a second injection substance and a second pressurizing substance in a liquid state and a gaseous state are pre-accommodated, and a second accommodating portion.
A jet flow generation unit that generates a jet flow from the first injection substance housed in the first storage unit and the second injection material housed in the second storage unit.
An injection port that injects the jet flow generated by the jet flow generation unit, and
Equipped with
The first injection substance and the first pressurizing substance in a liquid state are mixed.
The second injection substance and the second pressurizing substance in a liquid state are mixed.
By vaporizing at least a part of the first pressurizing substance in a liquid state in the first accommodating portion, the mixed first jetting substance and the first pressurizing substance in a liquid state are separated from each other. Pressed by the first pressurizing substance in a gaseous state and released from the first accommodating portion, at least a part of the second pressurizing substance in a liquid state is vaporized in the second accommodating portion. The mixed second injection substance and the second pressurizing substance in a liquid state are pressed by the second pressurizing substance in a gaseous state and released from the second accommodating portion. , Injection system. The first injection substance is a fuel, the second injection substance is an oxidant, and the jet flow generator burns the fuel by mixing the fuel and the oxidant. The injection system according to claim 6, which produces the jet flow. The sixth aspect of the present invention, wherein the heat capacity of the first injection substance is larger than the heat capacity of the first pressurizing substance, and the heat capacity of the second injection substance is larger than the heat capacity of the second pressurizing substance. The injection system described. The first accommodating portion accommodates a pressurizing substance different from the first pressurizing substance that presses the mixed first pressurizing substance and the first pressurizing substance in a liquid state. The second accommodating portion accommodates the mixed pressurizing substance different from the second pressurizing substance that presses the mixed second pressurizing substance and the second pressurizing substance in a liquid state. , The injection system according to claim 6. The temperature in the first accommodating portion is controlled to control the temperature in the first temperature control unit for vaporizing the first pressurizing substance in a liquid state, and the temperature in the second accommodating portion is controlled to be in a liquid state. The injection system according to claim 6, further comprising a second temperature control unit for vaporizing the second pressurizing substance. The tenth aspect of the present invention, wherein the first temperature control unit and / or the second temperature control unit includes a heater mounted over the entire circumference of the first accommodation unit and / or the second accommodation unit. Injection system. As the k-th accommodating portion in which the k-th jetting substance and the k-th pressurizing substance in the liquid state and the gaseous state are pre-accommodated, an integer k from 1 to n (n is an integer of 2 or more) is used. The first to nth accommodating parts given to each, and
A jet flow generation unit that generates a jet flow from the first to nth injection substances housed in the first to nth storage units, respectively.
It is provided with an injection port for injecting a jet flow generated by the jet flow generation unit.
The k-th injection substance and the k-th pressurizing substance in a liquid state are mixed.
By vaporizing at least a part of the kth pressurizing substance in a liquid state in the kth accommodating portion, the mixed kth injection substance and the kth pressurizing substance in a liquid state are separated. An injection system that pressurizes the inside of the first to nth accommodating portions, which are pressed by the kth pressurizing substance in a gaseous state and released from the kth accommodating portion.

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