JP3656092B2 - Precision machining method of variable thrust injector - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention is equipped with an attitude control propulsion unit (hereinafter referred to as a thruster) that is used for attitude control of an aircraft that travels in outer space such as a spacecraft and returns to the ground, and the attitude of the aircraft during navigation The present invention relates to a precision machining method for a thrust variable injector capable of variably controlling a propulsive force according to control.
[0002]
[Prior art]
In general, a thruster for navigating space, such as a spacecraft, and controlling the attitude of a flying vehicle that is operated to return to the ground, increases the accuracy of attitude control during missions in outer space, and improves mission accuracy. In addition, the minimum due to the restriction of the propellant composed of a propellant such as hydrogen peroxide (MMH) and the oxidant such as nitrogen peroxide (NTO) mounted in a finite volume space provided in the aircraft. -It is desirable to be able to control the attitude of an aircraft navigating in space over a long period of time by controlling the attitude with a small amount of propellant so that the impulse bit can be made small and a small thrust is generated.
[0003]
On the other hand, when an aircraft that has traveled in outer space returns to the ground, in the air navigation after the re-entry phase after entering the atmosphere, the attitude change due to aerodynamic disturbance becomes large, so it is short in time. However, in order to ensure the attitude control of the flying body and the trim of the airplane body, the thruster is required to generate a relatively large thrust for attitude control.
[0004]
For this reason, in an aircraft launched from the ground, navigating outer space, and returning to the ground again, in order to meet the thrust demands of thrusters necessary for attitude control in each flight phase, Two types of thrusters with different thrust capacities are installed, and they are used properly according to the thrust requirements required for attitude control in each flight phase.
[0005]
In other words, the conventional thruster uses an injection nozzle with a fixed hole diameter for the injector that injects the propellant and oxidant supplied from the propellant tank and oxidant tank into the combustion chamber individually and burns them. Therefore, it can be used only for generating a small thrust necessary for attitude control during space navigation and for generating a large thrust necessary for attitude control after the re-entry phase. Two types of thrusters, a thruster with a large-bore spray nozzle that can generate a small thrust and a thruster with a small-bore spray nozzle to generate a small thrust, are installed for attitude control in each flight phase. Depending on the required thrust, two types of thrusters are used separately.
[0006]
However, the installation of two types of thrusters leads to an increase in the number of parts and piping of the flying object, and there are restrictions on the installation location, and further, the reliability of the attitude control system is lowered and the flying object is reduced. However, there is a problem that the effective cargo to be mounted on the flying body, so-called payload, is reduced and the cost is increased.
[0007]
[Problems to be solved by the invention]
The present invention is different from the conventional injector that uses an injection nozzle having a constant hole diameter, and is used when it is necessary to generate a large thrust and a small thrust when a large thrust needs to be generated. In order to generate a large and small thrust, there are conventionally provided a platelet injector in which both of the small-diameter injection holes are provided on one plate and this plate is used as an injection nozzle as it is. The one that required a thruster can be reduced to one type of thruster, the number of parts and piping can be reduced, not only eliminating the restrictions on installation space, but also simplifying the attitude control system, It can be made reliable, and the weight can be reduced by reducing the number of parts, piping, etc., and the payload of the aircraft can be increased, and the cost can be reduced. And to provide a precision machining method of the thrust variable injectors can.
[0008]
[Means for Solving the Problems]
For this reason, the variable thrust injector manufactured by the precision machining method of the variable thrust injector of the present invention is the following means.
[0009]
(1) a large-diameter propellant flow path comprising a large-diameter oxidizer flow path for supplying an oxidizer having a large diameter and generating a large thrust to the combustion chamber, and a large-diameter propellant flow path for similarly supplying a propellant; A small-diameter propellant flow path comprising a small-diameter oxidizer flow path for supplying an oxidizer having a small diameter and generating a small thrust to the combustion chamber and a small-diameter propellant flow path for similarly supplying a propellant are provided, respectively. Propellant consisting of medicine is supplied to the combustion chamber via the large-diameter propellant flow path or small-diameter propellant flow path, respectively, and the propulsive force of the magnitude necessary for the attitude control of the aircraft navigating in space is required. A platelet injector is provided that can be generated when
[0010]
The platelet injector is formed of a disk-shaped thin plate as a whole, and a plurality of thin plates are stacked, and a large-diameter propellant flow path and a small-diameter propulsion respectively drilled in the thin plates stacked vertically. It is preferable that the agent flow paths are laminated and molded so as to communicate with the corresponding propellant flow paths, and have a predetermined thickness that allows the injection nozzle to be formed therein.
[0011]
Further, the large-diameter oxidant channel or the small-diameter oxidant channel provided in the platelet injector is provided closer to the axis side of the platelet injector than the large-diameter propellant channel or the small-diameter propellant channel. At the same time, it is preferable that the small-diameter oxidant flow path and the small-diameter propellant flow path are branched on the way from the supply surface side to the injection surface, respectively, so that they are separated from each other and opened.
[0012]
(2) It rotates about the axis of the platelet injector, opens and closes the large diameter propellant flow path or small diameter propellant flow path provided in the platelet injector, respectively, An injection manifold that supplies propellant introduced from outside was installed. The injection manifold should be able to open and close the large-diameter propellant flow path and small-diameter propellant flow path individually, and simultaneously open and close the large-diameter propellant flow path and the small-diameter propellant flow path. preferable.
[0013]
(3) The inside of the injection manifold rotates about the axis of the platelet injector, opens and closes the large-diameter oxidizer channel or the small-diameter oxidizer channel provided in the platelet injector, and opens the oxidizer flow An inner shaft for supplying an oxidant introduced from the outside through an oxidant introduction hole bored along the axis of the path was provided.
The inner shaft preferably allows the large-diameter propellant channel and the small-diameter oxidant channel to be opened and closed individually, and allows the large-diameter oxidant channel and the small-diameter oxidant channel to be simultaneously opened and closed. .
[0014]
(4) Large-diameter and small-diameter propellant supply for supplying the propellant supplied from the storage tank or the like to the large-diameter propellant channel or the small-diameter propellant channel opened by the rotation of the injection manifold, respectively. Large-diameter and small-diameter oxidizers that supply the oxidant supplied from the storage tank or the like to the oxidant introduction hole to the large-diameter oxidant flow path and the small-diameter oxidant flow path opened by the rotation of the path and the inner shaft, respectively. An outer shaft provided with a propellant supply path composed of a supply path was provided.
The propellant supply path is provided between an injection manifold that is independently rotated about the axis of the platelet injector and an inner shaft that is rotated inside the injection manifold. The outer shaft that is arranged coaxially with the injector is provided by being drilled.
[0015]
As described above, the variable thrust injector manufactured by the precision processing method of the variable thrust injector according to the present invention has the oxidant introduction hole formed along the axial center in the axial center portion above the platelet injector. An inner shaft that can rotate around the shaft center is provided, and a large-diameter oxidant flow path or small-diameter oxidizer provided in the oxidant introduction hole and the platelet injector when the inner shaft is rotated at a predetermined rotation. An oxidizing agent supply path that can communicate with the agent flow paths independently or simultaneously, and a large-diameter propellant flow path or a small-diameter propellant provided in the injection manifold and in the platelet injector when the injection manifold rotates a predetermined amount An outer shaft is provided to provide a propellant supply path that can communicate with the passage independently or simultaneously. Further, the outer shaft is rotated around the outer shaft at a predetermined rotation time. Open and close the opening of the propellant supply path The lid provided with that defines an injection manifold for introducing the propellant from the outside from propellant inlet, it consisted of the housing.
[0016]
The thrust variable injector manufactured by the precision processing method of the thrust variable injector according to the present invention needs to generate a large thrust for controlling the attitude of the flying object by means of the above-mentioned (1) to (4). Rotating the inner shaft communicates with the large-diameter oxidant supply path that communicates the oxidant introduction hole and the large-diameter oxidant flow path. It is necessary to communicate with the small-diameter oxidant supply path that communicates with the large-diameter propellant supply path that connects the inside of the injection manifold and the large-diameter propellant flow path by rotating the injection manifold. Therefore, a large amount of propellant is supplied into the combustion chamber by communicating with the small-diameter propellant supply path that connects the inside of the injection manifold and the small-diameter propellant flow path, requiring a large attitude change after the re-entry phase. For posture control when It is possible to generate a large thrust.
[0017]
In addition, when navigating in outer space, a large disturbance does not act on the flying object, and only a small thrust needs to be generated for attitude control. The agent introduction hole and the small-diameter oxidant flow path communicate with each other through a small-diameter oxidant supply path, and the injection manifold is rotated to close the large-diameter propellant flow path that opens in the injection manifold with an open / close lid. A small amount of propellant required for posture control can be supplied into the combustion chamber by connecting the inside and the small diameter propellant flow channel through a small diameter propellant supply channel.
[0018]
As a result, an aircraft that previously required two types of thrusters capable of generating large and small thrusts only needs to be equipped with one type of thruster, which reduces the number of parts and piping, and causes problems in installation space. In addition to eliminating the problem, the attitude control system can be simplified and reliable, and the weight can be reduced by reducing the number of parts and piping. The payload can be increased and the cost of the aircraft can be reduced.
[0019]
The precision machining method for the variable thrust thruster of the present invention employs the following means.
[0020]
(5) An injection hole in which a platelet injector provided in the thrust variable injector and configured to vary the propellant supplied to the combustion chamber is formed of a large diameter propellant channel and a small diameter propellant channel in a stainless steel thin plate The injection hole formation process which perforates and forms each.
[0021]
(6) The injection holes formed in the stainless steel thin plates are communicated with each other, and a plurality of thin stainless steel plates are stacked, and the small diameter propellant flow path is branched in the stacked stainless steel thin plates together with the function as an injection nozzle. The lamination process which makes the thing of the predetermined thickness which can do.
[0022]
(7) A joining step in which a plurality of thin stainless steel plates laminated in the laminating step are integrated by solid phase diffusion bonding.
The thin stainless steel plate is preferably formed of a thin disc-like one as a whole, and the large-diameter oxidant channel or the small-diameter oxidant channel is a large-diameter propellant channel or a small-diameter propellant channel, respectively. The small-diameter oxidant flow path and the small-diameter propellant flow path should be branched in the middle of lamination and opened separately from each other in the combustion chamber. It is preferable to make it possible.
[0023]
Thereby, a so-called injection hole having a large diameter propellant flow path, a large diameter oxidant flow path, a small diameter propellant flow path, and a small diameter oxidant flow path formed in the platelet injector has a hole diameter of 1 mm or less. In addition, even if the shortest injection hole interval is 0.3 mm to 0.5 mm, the required processing accuracy can be sufficiently cleared.
Further, at the time of joining when forming the platelet injector by laminating thin stainless plates, the joining can be performed without filling the small-diameter injection holes, and the dimensional change due to the joining can be made small.
[0024]
Furthermore, since the injection holes that are individually drilled in the stainless steel plate are connected and laminated, it is easy to form the injection holes that are formed in the platelet injector, and it is difficult to machine. The performance of the variable thrust injector can be improved.
[0025]
DETAILED DESCRIPTION OF THE INVENTION
DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Embodiments of a precision machining method for a variable thrust injector according to the present invention and a manufacturing method for a platelet injector used in a variable thrust injector manufactured by a precision machining method for a variable thrust injector according to the present invention will be described below with reference to the drawings. This will be explained based on this.
FIG. 1 is a cross-sectional view showing the basic structure of a thrust variable thruster provided with a first embodiment of the variable thrust injector of the present invention.
[0026]
As shown in the drawing, the thrust variable thruster is supplied with a thrust variable injector 2 that controls the flow rate of a propellant 6 composed of a propellant 4 such as MMH and an oxidant 5 such as NTO and supplies the propellant 6 to the combustion chamber 7. The thrust generator 3 generates high-temperature and high-pressure combustion gas from the propellant 6 and injects it from the nozzle 8 to generate thrust.
In the figure, reference numeral 9 denotes a gear driven by a hydraulic actuator or the like for rotating an inner shaft 10 and a housing 11 which will be described later.
[0027]
2 is a cross-sectional view showing details of the thrust variable injector 2 in FIG. 1, and FIG. 2 (a) is a diagram showing a large-diameter propellant flow path 22 and a large-diameter oxidizer on the left side constituting the large-diameter propellant flow path 21. FIG. 2B is a longitudinal sectional view showing a state in which the flow channel 23 is opened, and a state in which the small diameter propellant flow channel 25 and the small diameter oxidant flow channel 26 forming the small diameter propellant flow channel 24 are opened on the right side. Fig. 2A is a transverse sectional view at the time of a small thrust in the state on the right side of Fig. 2A in the arrow AA shown in Fig. 2A, and Fig. 2C is an arrow AA shown in Fig. 2A. FIG. 3 is a transverse sectional view at the time of large thrust in the state on the left side of FIG.
In FIG. 2, the arrangement of the oxidant supply port including the oxidant introduction hole and the oxidant vent hole in the variable thrust injector 2 shown in FIG. 1 is changed.
[0028]
As shown in FIG. 2, the variable thrust injector 2 includes a small-diameter propellant channel 24, a large-diameter propellant channel 22, and a large-diameter oxidant channel composed of a small-diameter propellant channel 25 and a small-diameter oxidant channel 26. Each of the large-diameter propellant passages 21 is formed by controlling the flow rate of the propellant 6 and injecting it into the combustion chamber 7 in accordance with the magnitude of thrust necessary for controlling the attitude of the flying object. A platelet injector 10 having a thickness capable of forming a nozzle by laminating disk-shaped thin plates fixed to the inner peripheral surface of the housing 14 is provided.
[0029]
The propellant flow path drilled in the platelet injector 10 is an oxidant flow path, that is, the large diameter oxidant flow path 23 and the large diameter propellant flow path 22 and the small diameter propellant flow path 25. Both the small-diameter oxidant flow path 26 and the small-diameter propellant flow path 25 and the small-diameter oxidant 26 opened on the supply surface 38 of the platelet injector 10 are arranged on the outer peripheral side of FIG. As shown in FIG. 3, which is a detailed view of the A part, the inside of the platelet injector 10 is bifurcated so that two openings are formed on the injection surface 39.
[0030]
Also in this case, the small-diameter propellant flow path 25 that opens to the injection surface 39 is arranged so as to be paired with the outside of the small-diameter oxidant flow path 26.
Further, a small-diameter oxidant introduction hole 28 standing at the axial center of the platelet injector 10 and drilled along the axial center, and a large-diameter oxidant introduction hole 29 drilled in parallel with the axial center. An inner shaft 11 having a plurality of oxidant introduction holes 27 formed therein is provided.
[0031]
As described above, the inner shaft 11 can be rotated around its axis by the gear 9 shown in FIG.
Similarly, the outer side of the inner shaft 11 is concentric with the platelet injector 10, and a thrust bearing 39 and an O-ring 40 are interposed between the inner shaft 11 and the rotating inner shaft 11. A small-diameter oxidant supply path 31 that is slidable and communicates with the small-diameter oxidant introduction hole 28 and the small-diameter oxidant flow path 26 and constitutes an oxidant supply path 30 together with a large-diameter oxidant supply path 34 to be described later. An injection manifold 13 and a small-diameter propellant flow path 25, which will be described later, communicate with each other, and together with a large-diameter propellant supply path 35, which will be described later, a small-diameter propellant supply path 32 and a large-diameter oxidant. A large-diameter oxidant supply path 34 that communicates the introduction hole 24 and the large-diameter oxidant flow path 23 and a large-diameter propellant supply path 35 that communicates the injection manifold 13 and the large-diameter propellant flow path 22 are bored inside. The outer shaft 12 is provided To have.
[0032]
In the present embodiment, the outer shaft 12 is fixed to the platelet injector 10, and the oxidant supply path 30 and the large diameter oxidant flow path 23, the small diameter oxidant flow path 26 and the propellant supply path 33 and the large diameter propulsion. Communication with the medicine flow path 22 and the small diameter propellant flow path 25 is maintained.
Further, on the outer side of the outer shaft 12, an O-ring 40 is interposed between the lower housing that fixes the outer surface of the platelet injector 10 on the inner peripheral surface and the outer peripheral surface of the outer shaft 10. And a housing 14 in which an injection manifold 13 communicating with the propellant supply passage 33 is formed on the outer periphery of the outer shaft 12 between the lower housing and the upper housing. Yes.
[0033]
In addition, a propellant vent hole 15 for releasing the excess propellant 4 to the outside is formed in the upper housing of the housing 14, and the inner peripheral portion of the defined injection manifold has a constant pitch in the circumferential direction. An opening / closing lid 16 is provided for opening and closing the injection manifold 13 and the propellant supply passage 33 that opens to the injection manifold 13 by the rotation of the upper housing.
Further, a block 18 formed in a propellant supply hole 17 for supplying the propellant 4 from the outside into the injection manifold 13 is provided on the outer periphery of the lower portion of the housing 14 where the injection manifold 13 is provided. The inner peripheral surface of the block 18 that is interposed between the outer cylinder 19 to be formed and not provided with the propellant supply hole 17 closes the outer periphery of the injection manifold 13 defined in the housing 14. I have to.
[0034]
Further, above the housing 17, the upper end of the inner shaft 11 passes through the center portion, and the oxidant supply port 36 for supplying the oxidant 5 and the oxidant vent hole for discharging the excess oxidant 5 to the outside. An upper lid 20 provided with 37 is provided.
[0035]
In the thrust variable injector, when a large thrust is required for the attitude control of the flying object, both the large-diameter propellant supply path 35 and the small-diameter propellant supply path 32 are opened as shown in FIG. In addition, when it is necessary to open both the large-diameter oxidant supply path 34 and the small-diameter oxidant supply path 31, and when a small thrust is required, a small-diameter propellant supply path as shown in FIG. It is necessary to open only the small diameter oxidant 31 while opening only 32.
[0036]
Thus, in the variable thrust thruster, it is necessary to secure the flow paths of both the propellant 4 and the oxidizer 5 for both the large thrust and the small thrust, and the opening / closing operation is required, and the flow path and the opening / closing control are complicated. .
[0037]
However, since the variable thrust injector 2 according to the present embodiment is configured as described above, the large-diameter propellant supply for large thrust and small thrust is achieved by rotating the injection manifold 13 that supplies the propellant 4. The propellant injection hole comprising the large diameter propellant flow path 22 and the small diameter propellant flow path 25 provided in the platelet injector 10 is opened and closed, and the inner shaft 11, the large-diameter oxidant supply path 34 and the small-diameter oxidant supply path 31 for large thrust and small thrust, in other words, the large-diameter oxidant flow path 23 provided in the platelet injector 10 and It is possible to make the thrust variable by opening and closing the oxidant injection hole composed of the small-diameter oxidant channel 26.
[0038]
Therefore, when it is necessary to generate a large thrust for posture control, the large-diameter oxidant supply path 34 that connects the oxidant introduction 27 and the large-diameter oxidant flow path 23 by rotating the inner shaft 11 is used. The small-diameter oxidant channel 26 communicates with the small-diameter oxidant supply channel 31, and the large-diameter communicating the inside of the injection manifold 13 and the large-diameter propellant passage 22 by rotating the injection manifold 13. A large amount of propellant 6 is supplied into the combustion chamber 7 by communicating with the propellant supply path 35 and the small-diameter propellant flow path 25 with the small-diameter propellant supply path 32. It is possible to generate a large thrust for posture control when a large posture change is required.
[0039]
When only a small thrust needs to be generated, the inner shaft 11 is further rotated so that the oxidant introduction hole 27 and the small diameter oxidant flow path 26 communicate with each other through the small diameter oxidant supply path 31 and the injection manifold. By further rotating 13, the large-diameter propellant flow path 22 that opens to the injection manifold 13, that is, the large-diameter propellant supply path 35 is closed by the lid 16 that opens and closes, and the inside of the injection manifold 13 is small-diameter propellant. A small amount of propellant 6 required for posture control can be supplied into the combustion chamber 7 by communicating only the flow path 25 with a small-diameter propellant supply path 32.
[0040]
As a result, an aircraft that previously required two types of thrusters capable of generating large and small thrusts need only be equipped with one type of thrust variable thruster 1, reducing the number of parts and piping, and installing space. The above problem can be solved, and the attitude control system can be simplified and made highly reliable.
Further, since only one type of thrust variable thruster 1 needs to be installed, the weight can be reduced by reducing the number of parts, piping, etc., thereby increasing the payload of the flying object, and the flying object. The cost can be reduced.
[0041]
Next, the thin plate used for the thrust variable injector 2 described above is laminated to form an injection nozzle, and the platelet injection is formed so that the small-diameter propellant channel 24 can be branched into two. A first embodiment of the manufacturing method of the vessel 10 will be described.
[0042]
The disc-shaped thin plate forming the plate injector 10 shown in FIG. 4 was used as a SUS329J1 type duplex stainless steel (hereinafter referred to as a stainless thin plate) 42 material.
In order to manufacture the platelet injector 10 with this material, as shown in FIG. 5, a large-diameter propellant flow path 22, a large-diameter oxidant flow path 23, and a small-diameter propellant flow path 25 are previously formed by laser processing and photoetching. A so-called injection hole 41 composed of the small-diameter oxidant channel 26 is formed.
[0043]
Next, as shown in FIG. 6, the injection holes 41 formed in the stainless steel thin plate 42 in which the injection holes 41 are formed are stacked so that the injection holes 41 communicate with those formed in the upper and lower thin plates. The platelet injector 10 in which the complex large-diameter propellant flow path 21 and the small-diameter propellant flow path 24 (hereinafter collectively referred to as injection holes 41) of the oxidizer 5 and the propellant 4 were formed by bonding. .
[0044]
Since the hole diameter of the injection hole 41 of the platelet injector 10 is φ1.0 mm or less and the interval between the injection holes 41 is about 0.3 to 0.5 mm at the shortest, processing accuracy of several tens of μm level is required. The
In addition, there are two types of stainless steel sheet diffusion bonding methods, liquid phase diffusion bonding and solid phase diffusion bonding, and liquid phase diffusion bonding is superior in terms of precision bonding, but the platelet injector in the present embodiment In the case of 10, the injection hole diameter is extremely small as described above, so it is highly likely that the liquid phase diffusion bonding will be buried at the time of bonding, so a precise solid-phase bonding method with little change in the size of the injection hole diameter during diffusion bonding has been developed. The platelet injector was manufactured by this joining method.
[0045]
In addition, the platelet injector 10 manufactured by applying the stainless steel thin plate 43 as the present material has a structure control (equal axis microstructure) in the (δ + γ) two-phase temperature range of the present material as shown in FIG. Solid phase diffusion bonding was performed in the temperature range.
As a result, since this material exhibits superplastic properties in the (δ + γ) two-phase temperature range due to the equiaxed refinement of the structure, it aims at precision bonding with low pressure for a short time using the properties.
[0046]
FIG. 8 shows a cross-sectional microstructure obtained by solid phase diffusion bonding of this material under the conditions of a bonding temperature of 1000 ° C. and a bonding time of 10 minutes.
Although the interface of the laminated thin plate is located in the center of the photograph, it can be seen that there is no unbonded portion and the bonding is completed.
[0047]
【The invention's effect】
As described above, according to the thrust variable injector manufactured by the precision processing method of the thrust variable injector of the present invention, the large-diameter oxidant channel for supplying the oxidant and the large-diameter propellant for supplying the propellant. A platelet injector having a small-diameter propellant channel formed by a small-diameter propellant channel comprising a large-diameter propellant channel comprising a channel, a small-diameter oxidant channel supplying oxidant and a small-diameter propellant channel supplying propellant, An injection manifold that rotates around the axis of the platelet injector and supplies the propellant introduced inside to the combustion chamber by opening and closing the large-diameter propellant channel or small-diameter propellant channel, coaxial with the inside of the injection manifold The oxidant introduced from the oxidant introduction hole formed around the shaft center and rotated around the axis of the platelet injector is supplied to the large-diameter oxidant channel or the small-diameter oxidant stream. To open and close the passage and supply to the combustion chamber A propellant supply passage that is interposed coaxially between the injection manifold and the inner shaft and supplies the propellant to the large-diameter propellant flow path or the small-diameter propellant flow path opened by the rotation of the injection manifold. And an outer shaft provided with an oxidant supply path for supplying the oxidant to the large-diameter oxidant channel or the small-diameter oxidant channel opened by the rotation of the inner shaft, respectively. .
[0048]
Thus, when it is necessary to generate a large thrust, the inner shaft is rotated to communicate with the large-diameter oxidant supply path that communicates the oxidant introduction hole and the large-diameter oxidant flow path. The large amount of propellant is supplied into the combustion chamber by generating a large thrust by communicating with the large-diameter propellant supply passage that communicates the inside of the injection manifold and the large-diameter propellant passage by rotating it can.
[0049]
When generating a small thrust, the oxidant introduction hole and the small-diameter oxidant flow path are communicated with each other by a small-diameter oxidant supply path by rotating the inner shaft, and the injection manifold is rotated by rotating the injection manifold. The large-diameter propellant channel that opens to the inside is closed with an open / close lid, and the small-diameter propellant channel is connected to the inside of the injection manifold through the small-diameter propellant supply channel, so that a small amount of propellant is required for posture control in the combustion chamber Can be supplied.
[0050]
As a result, an aircraft that previously required two types of thrusters capable of generating large and small thrusts only needs to be equipped with one type of thruster, which reduces the number of parts and piping, and causes problems in installation space. In addition to eliminating the problem, the attitude control system can be simplified and reliable, and the weight can be reduced by reducing the number of parts and piping. And the cost of the flying object can be reduced.
[0051]
Further, in the thrust variable injector manufacturing method of the present invention, the platelet injector provided in the thrust variable injector has an injection hole formed of the large-diameter propellant channel and the small-diameter propellant channel in a thin stainless plate. Each of the injection hole forming step for drilling, the stacking step of stacking a plurality of the stainless thin plates by communicating the spray holes drilled in the stainless thin plate, and the stainless thin plate stacked by the stacked holes as a solid phase A bonding process for diffusion bonding is adopted.
[0052]
As a result, even if the so-called injection holes that are perforated in the platelet injector have a hole diameter of 1 mmφ or less, or even when the shortest injection hole interval is extremely small, the required processing accuracy is achieved. It can be.
Further, when joining when forming a platelet injector by laminating thin stainless plates, the injection can be made without filling the injection hole with a small hole diameter, and the dimensional change of the hole diameter at the time of joining can be made small.
[0053]
Furthermore, since the injection holes that are individually drilled in the stainless steel plate are connected and laminated, it is easy to form the injection holes that are formed in the platelet injector, and it is difficult to machine. Therefore, the performance of the variable thrust injector can be improved.
[Brief description of the drawings]
FIG. 1 is a cross-sectional view showing a basic structure of a thrust variable thruster having a first embodiment of a variable thrust injector manufactured by a precision processing method for a variable thrust injector according to the present invention;
2 is a cross-sectional view showing details of the thrust variable injector in FIG. 1. FIG. 2 (a) shows a large-diameter propellant flow path and a large-diameter oxidant flow path on the left side constituting a large-diameter propellant flow path. FIG. 2 (a) is a longitudinal sectional view showing a state in which the small-diameter propellant channel and the small-diameter oxidant channel forming the small-diameter propellant channel are opened. 2A is a transverse cross-sectional view at the time of a small thrust in the state on the right side of FIG. 2A, FIG. 2C is the view of FIG. 2A in the arrow AA shown in FIG. Cross-sectional view at the time of large thrust in the left side state,
3 is a detailed cross-sectional view of a portion A shown in FIG.
4 is a view showing the platelet injector shown in FIG. 2, FIG. 4 (a) is a view showing a supply surface, and FIG. 4 (b) is a cross-sectional view taken along line BB shown in FIG. 4 (a). FIG. 4 (c) is a view showing the injection surface,
FIG. 5 is a diagram showing an injection hole forming process in the manufacturing process of the platelet injector shown in the figure;
FIG. 6 is a diagram showing a stacking process and a joining process in the manufacturing process of the platelet injector shown in FIG.
FIG. 7 is a quasi-two-element phase diagram of a stainless steel sheet for producing a platelet injector,
FIG. 8 is a cross-sectional microstructure photograph in which stainless steel thin plates are laminated and solid phase diffusion bonded.
[Explanation of symbols]
1 Thrust variable thruster
2 Thrust variable injector
3 Thrust generator
4 propellant
5 Oxidizing agent
6 propellant
7 Combustion chamber
8 nozzles
9 Gear
10 Platelet injector
11 Inner shaft
12 Outer shaft
13 Injection manifold
14 Housing
15 Propellant vent hole
16 Opening and closing lid
17 Propellant supply port
18 blocks
19 outer cylinder
20 Top lid
21 Large diameter propellant flow path
22 Large diameter propellant flow path
23 Large diameter oxidant flow path
24 Small-diameter propellant flow path
25 Small-diameter propellant flow path
26 Small-diameter oxidant flow path
27 Oxidant introduction hole
28 Small-diameter oxidant introduction hole
29 Large-diameter oxidant introduction hole
30 Oxidant supply path
31 Small-diameter oxidant supply path
32 Small-diameter propellant supply path
33 Propellant supply channel
34 Large-diameter oxidant supply path
35 Large-diameter propellant supply channel
36 Oxidant supply port
37 Oxidant vent hole
37 Supply side
38 Injection surface
39 Thrust bearing
40 O-ring
41 injection hole
42 Stainless steel sheet

Claims (2)

In a thrust variable injector that controls the flow rate of a propellant composed of an oxidant and a propellant and supplies the propellant to the combustion chamber, a large-diameter oxidant channel that supplies the oxidant to the combustion chamber and the propellant are supplied A large-diameter propellant channel comprising a large-diameter propellant channel, a small-diameter oxidant channel for supplying the oxidant to the combustion chamber, and a small-diameter propellant channel comprising a small-diameter propellant channel for supplying the propellant. Respectively, and the propellant introduced inside opens and closes the large-diameter propellant channel or the small-diameter propellant channel. An injection manifold that is supplied to the combustion chamber, and an oxidant introduction hole that is coaxially installed inside the injection manifold and rotates about the axis of the platelet injector and is drilled along the axis. Introduced oxidizer An inner shaft that opens and closes the large-diameter oxidant flow path or the small-diameter oxidant flow path and supplies the combustion chamber, and the injection manifold and the inner shaft are coaxially interposed. The propellant supply path for supplying the propellant to the large-diameter propellant flow path or the small-diameter propellant flow path opened by movement, and the large-diameter oxidant flow path opened by rotation of the inner shaft Alternatively, a variable thrust thruster characterized in that an outer shaft provided with an oxidant supply path for supplying the oxidant to the small-diameter oxidant flow path is provided. An injection hole forming step in which the platelet injector provided in the thrust variable injector has an injection hole formed of the large-diameter propellant channel and the small-diameter propellant channel in a stainless steel thin plate; and the stainless steel thin plate Each of the injection holes formed in each of the holes is connected to each other, and a plurality of the stainless thin plates are laminated, and a joining step of solid-phase diffusion bonding the stainless thin plates laminated in the laminating step. The precision machining method of the thrust variable injector according to claim 1, wherein the thrust is variable.

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