JP2003240500A - Side thruster for flying body - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide large lateral thrust by the same gas generation amount. <P>SOLUTION: A plurality of nozzles 4A-4D is arranged within a plane orthogonal to a body center axis, and a flow control valve 6 is provided to conduct variable control for gas flow-rates in the respective nozzles 4A-4D while distributing high-pressure gas from a chamber side to the respective nozzles 4A-4D. In the flow control valve 6, an opening area in each of the nozzles 4A-4D is variably controlled as a function of a position of each pintle 8 driven by a cam 9 to open and close each nozzle throat part 7, and is set to keep a fixed ratio of total opening area of the nozzle throat parts 7 to the total number of the nozzles all the time. The flow-rate corresponding to total gas flow-rate supplied from the chamber side is allowed to flow to the one nozzle selected optionally. <P>COPYRIGHT: (C)2003,JPO

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a side thruster for a flying vehicle, and in particular, it is mounted on a flying vehicle such as a rocket flying in or out of the atmosphere, and is used in a direction orthogonal to the center axis of the vehicle when changing the trajectory. The present invention relates to a so-called side thruster in which thrust of the same direction is generated by injecting high-pressure gas into the vehicle to control the attitude or trajectory of the airframe.

[0002]

2. Description of the Related Art As a technique related to a side thruster, for example, Japanese Unexamined Patent Publication No. 2000-346598 and Japanese Unexamined Patent Publication No.
The one described in Japanese Unexamined Patent Publication No. 0-103156 has been proposed.

In the former type, four nozzles are radially arranged in a plane orthogonal to the central axis of the machine at 90 ° phase, that is, a total of four nozzles are arranged so that the two nozzles face each other and face each other. By moving the pintle that variably controls the opening area of the two nozzle throat parts,
It is designed to control lateral thrust. That is,
Since the two nozzles are arranged on the same axis and the two nozzle facing axes are set to be orthogonal to each other, each pintle is slidably displaced along the nozzle facing axis. .

In the latter type, a spherical bearing type valve member is arranged at the center of four nozzles arranged in the same manner as described above, and the valve member is rotated in two directions in which the nozzles are opposed to each other. By displacing, the opening area of each nozzle throat is variably controlled.

[0005]

In the prior art as described above, both the former and latter structures are variably controlled as a pair of opening areas of the throat portions of two nozzles facing each other. Therefore, increasing the opening area of either one of the two nozzles facing each other will decrease the opening area of the other nozzle throat accordingly. As a result, the sum of the opening areas of the throat portions of the two nozzles facing each other is always kept constant (1/2 of the sum of the opening areas of the throat portions of all nozzles), and by extension, the throat portions for the total number of nozzles are maintained. It is set so that the sum of the opening areas is always constant. This means that the maximum sum of the nozzle throat areas for generating thrust in a specific direction is only half the sum of the nozzle throat areas for the total number of nozzles.

Therefore, when a thrust force is to be generated along one of the two nozzle-opposing axes that are orthogonal to each other as a so-called single-axis operation, the two nozzle-opposing axes on the other nozzle-opposing axis will be used. To maintain the neutral state, each nozzle consumes 1/4 of the total number of nozzles, and as a result, the amount of gas that is effectively used to generate thrust is only half of the total amount of gas generated. The thrust obtained is small relative to the amount of gas generated, resulting in extremely low efficiency. On the other hand, in order to secure a necessary and sufficient amount of gas generation, there is no method other than increasing the number of propellants to be mounted, and the weight of the propellant increases, which is not preferable.

In addition, based on the former structure, some pintles are individually devised so that the opening area of the throat portion of each nozzle can be independently and freely changed. Has been done.

However, in this case, it is necessary to make the pintle driving mechanism independent for each pintle.
In addition to increasing its weight and occupying space, it also complicates the structure, and since each pintle moves independently, the total opening area of the nozzle throat part is not always constant, and the combustion on the gas generator side The pressure becomes unstable, and the controllability and responsiveness are deteriorated.

The present invention has been made in view of the above problems, and it is premised that the total opening area of the flow rate adjusting ports for the total number of nozzles is always maintained at a constant size. The maximum value of the effective opening area for thrust generation can be made equal to the total opening area of the flow adjustment ports for the total number of nozzles, i.e., one nozzle selected arbitrarily is supplied from the gas generator side. It is intended to provide a structure in which all the gas flow rates can be made to flow and a stable and larger thrust can be obtained.

[0010]

According to a first aspect of the present invention, a plurality of nozzles, which open toward the outer peripheral surface of the machine body, are arranged radially in a plane orthogonal to the machine body center axis. At the same time, it is premised on a side thruster of a flying body that is configured to generate thrust in a direction orthogonal to the central axis of the airframe by injecting high-pressure gas from any nozzle to perform attitude control or trajectory control.

A flow control valve for variably controlling the gas flow rate at each nozzle while distributing the high-pressure gas from the gas generator side to each nozzle is provided, and this flow control valve is a valve for opening and closing the flow rate adjusting port. The opening area of the flow rate adjusting ports of each nozzle is variably controlled as a function of the position of the body, while the total opening area of the flow rate adjusting ports corresponding to the total number of nozzles is always set to a constant size. In addition, the flow rate of all the gas supplied from the gas generator side can be made to flow to one arbitrarily selected nozzle.

As the gas generator, for example, a known structure for generating high-pressure gas by burning the mounted solid propellant in the chamber is used.

As for the arrangement of the nozzles, a total of four nozzles are arranged so that the two nozzles face each other as in the conventional case. However, the total number of nozzles is not necessarily limited to four.

In this case, as described in claim 2, the valve element is independent for each nozzle, and each valve element is individually opened and closed by a single cam member shared by the plurality of valve elements. Or the claim 3
As described above, each nozzle shares a single valve body, and by opening and closing this valve body, the opening area of the flow rate adjusting port of each nozzle is individually and variably controlled. It is desirable to simplify drive control.

Then, while the opening area of the flow rate adjusting port of each nozzle is variably controlled as a function of the position of the valve body that opens and closes the flow rate adjusting port, the total opening area of the flow rate adjusting ports corresponding to the total number of nozzles is always large. In addition, in order to allow all the gas flow rates supplied from the gas generator side to flow to one arbitrarily selected nozzle, the cam according to claim 2 according to its characteristics. The profile shape of the member is set to a three-dimensional shape in advance, or the shape of the flow rate adjusting port of the orifice, which is the valve element, is set in the same manner.

The flow rate adjusting ports described in claims 2 and 3 are the throat portion of each nozzle as described in claim 4, and the valve body variably controls the effective opening area of the nozzle throat portion. It is desirable to simplify the structure.

Therefore, in the inventions according to claims 1 to 4, the opening amount of the nozzle throat, which is the flow rate adjusting port of each nozzle, is variably controlled as a function of the position of the valve element, so that the nozzles corresponding to the total number of nozzles are provided. The total opening area of the throat part is always maintained to be a constant size, and it is possible to flow all gas flow rates supplied from the gas generator side to one nozzle arbitrarily selected as needed. become able to. This means that the maximum sum of nozzle throat areas for thrust generation in a specific direction is equal to the sum of nozzle throat areas for the total number of nozzles. The maximum value of the total sum of the nozzle throat areas for is only half of the total sum of the nozzle throat areas corresponding to the total number of nozzles.

According to a fifth aspect of the present invention, the valve body according to the fourth aspect is a pintle that moves back and forth in the axial direction of the nozzle to open and close the nozzle throat portion, and each pintle moves forward and backward in the central axis direction of the machine body. It is characterized in that it is adapted to be opened and closed by a movable and rotatable cam member.

The invention according to claim 6 is the same as claim 4
The valve body described in (1) is a shutter that can be rotated about an axis parallel to the center axis of the machine body, and each shutter can be moved forward and backward in the axial direction of the machine body and can be opened and closed by a rotatable cam member. It is characterized by becoming.

Therefore, in the inventions according to the fifth and sixth aspects, even if the pintle or shutter functioning as a valve element is independent for each nozzle, a common cam shared by each pintle or shutter is provided. 2 parts
By driving in the direction, each pintle or shutter is independently displaced, and as a result, the total opening area of the nozzle throat part for the total number of nozzles is always maintained at a constant size, as well as necessary. Accordingly, the flow rate of all the gas supplied from the gas generator side can be made to flow to one arbitrarily selected nozzle.

According to a seventh aspect of the invention, the valve body according to the fourth aspect is an orifice arranged on the same axis as the central axis of the machine body and having orifice passages corresponding to the respective nozzle throat portions. It is characterized in that the amount of overlap between each orifice passage and the nozzle throat portion is variably controlled by moving this orifice forward and backward along the central axis of the machine and rotating it.

Therefore, according to the invention described in claim 7, the overlap amount of each orifice passage and the nozzle throat portion is variably controlled based on the forward / backward movement of the orifices, so that the nozzle throat portions corresponding to the total number of nozzles are similarly controlled. So that the total opening area of the gas generator is always maintained at a constant size, and all gas flow rates supplied from the gas generator side can be made to flow to one nozzle arbitrarily selected as needed. become.

In the second to seventh aspects, it is particularly preferable that the valve element and the cam member are made of a heat-resistant material as in the eighth aspect, in the case of long-time operation.

[0024]

According to the invention described in claims 1 to 4, the flow rate control valve for distributing the high pressure gas to each nozzle is a valve body for opening and closing a flow rate adjusting port or a nozzle throat portion which is a flow rate adjusting port. The opening area of the nozzle is variably controlled as a function of the position of the nozzle, so that the total opening area of the flow rate adjusting ports or nozzle throats for the total number of nozzles is always a constant size, and one selected arbitrarily. The flow rate of all the gas supplied from the gas generator side to the nozzle can be made to flow. Therefore, the maximum sum of the flow rate adjustment ports or nozzle throat areas for generating thrust in a specific direction is equivalent to the sum of the flow rate adjustment ports or nozzle throat areas for the total number of nozzles. The efficiency is remarkably improved, a larger thrust can be generated, the combustion and pressure on the gas generator side are stabilized, and the controllability is improved.

Particularly, according to the invention described in claim 2, independent valve bodies for each nozzle share a single cam member for driving, and according to the invention described in claim 3, If
Since each nozzle shares a single valve body, there is an advantage that the number of parts can be reduced and the mechanical structure can be further simplified.

According to the fifth and sixth aspects of the present invention, the pintle or the shutter functioning as a valve element is driven by a cam member that is movable back and forth and rotatable. By independently moving the motor back and forth and rotating it independently of each other, the pintle or shutter, which is the valve element, can follow the movement of the cam member faithfully, and the opening area of the nozzle throat can be controlled variably. There is an advantage that can be done accurately.

According to the invention described in claim 7, the forward and backward movement and rotation of the orifice functioning as a valve body common to each nozzle are individually performed by mutually independent motors or the like. In addition to accurately controlling the opening area of the nozzle throat with a small number of parts, there is an advantage that the structure of the flow control valve can be further simplified.

[0028]

DESCRIPTION OF THE PREFERRED EMBODIMENTS FIGS. 1 to 8 show the first preferred embodiment of the present invention.
1 is a diagram showing an embodiment of the present invention, FIG. 1 is an overall schematic configuration explanatory diagram showing an example of a flying body, and FIG.
3 is an enlarged sectional view taken along line a, FIG. 3 is a sectional view taken along line bb of FIG. 2, and FIG. 4 is a right side view of FIG.

As shown in FIGS. 1 to 4, a solid propellant is loaded inside a fuselage 2 of a flying body 1 and a chamber 3 serving as a gas generator which also serves as a combustion chamber is arranged. On the side and the center axis of the machine (machine axis) C
A total of four nozzles 4A to 4D, which open toward the outer peripheral side of the machine body, are arranged radially in a 90-degree phase around the machine body central axis C in a plane orthogonal to. Of these four nozzles 4A to 4D, the nozzles 4A and 4C face each other on the nozzle facing axis P1, and the remaining nozzles 4B and 4D also face each other on the nozzle facing axis P2. P1 and P2 are orthogonal to each other. The nozzles 4A to 4D are connected to the chamber 3 via independent gas passages 5, and the flow rate adjusting valve 6 is provided so that the nozzles 4A to 4D share each other. As described above, the combustion gas generated by the combustion in the chamber 3 is distributed to the nozzles 4A to 4D through the gas passage 5 and is injected from the nozzles 4A to 4D.

The flow rate adjusting valve 6 opens and closes the nozzle throat portion 7 which is individually provided in each gas passage 5 and substantially functions as a flow rate adjusting port, and its opening area (opening degree).
The pintle 8 is a valve body for variably controlling the pintle 8 and a three-dimensional cam 9 arranged in the center position of the pintle array so as to be shared by the pintles 8. Each pintle 8 can move back and forth along the nozzle facing axis P1 or P2, and the contact portion at one end thereof is in contact with the profile surface of the cam 9. The cam 9 is supported on both sides by a bearing member 10 so that the cam 9 can rotate around the machine body central axis C and can move back and forth along the machine body central axis C,
The rotation of the cam 9 is performed by the servo motor 11 and the cam 9
Further, the forward and backward movements are independently performed by different servo motors 12.

More specifically, a non-rotating screw shaft 13 that forms a ball screw together with an inner cylinder member 14 to be described later is supported on both sides of the bearing member 10, and this screw shaft 13 supports the ball screw. The inner cylinder member 14 that functions as a nut side member is screwed together, and the cam 9 is supported by the inner cylinder member 14 so as to be relatively rotatable. As shown in FIG. 4, an arm 15 integral with the cam 9 is extended to the cam 9, and the arm 15
A ball screw 16 having a screw shaft as an output shaft on the side of the servo motor 11 and a nut member on the side of the arm 15 is interposed between and the servo motor 11 for rotational driving. Therefore, the cam 9 is driven to rotate by the activation of the servo motor 11.

Similarly, an arm 18 integral with the inner cylinder member 14 is extended to the inner cylinder member 14, and an output shaft on the side of the servo motor 12 is provided between the arm 18 and the servo motor 12 for advancing and retracting. A ball screw 17 having a screw shaft as a shaft and a nut member on the arm 18 side is interposed.
Therefore, by starting the servomotor 12, the inner cylinder member 1
When the inner cylinder member 14 is rotated, the inner cylinder member 14 moves forward and backward due to the screw engagement with the screw shaft 13, and the inner cylinder member 1
4, the cam 9 moves forward and backward in the direction of the central axis C of the machine. At this time, since the cam 9 is constrained by the arm 15 and the ball screw 16, it does not rotate together with the inner cylinder member 14.

The profile of the cam 9 has a three-dimensional three-dimensional shape as shown in FIGS. 5 and 6, for example, and the servo motor 12 rotates in the same manner as the rotation of the cam 9 by the servo motor 11.
By using the forward and backward movement of the cam 9 singly or both in combination, the respective pintles 8 individually move forward and backward,
The corresponding nozzle throat section 7 is opened and closed to variably control the opening degree.

Here, assuming that the rotating direction of the cam 9 is X and the moving direction of the cam is Y, FIG. 7 shows a thrust pattern when the gas generation amount is "1". That is, the circle R with the distance "1" from the center in the figure shows the pattern when the generated gas can be used with 100% efficiency in all directions (the distance from the center is 1). In the case of the prior art, as shown by the symbol Q2, 1 is set in the X and Y directions
It shows that only a thrust pattern of / 2 can be obtained.
The X direction in FIG. 7 corresponds to the nozzle facing axis P1,
It coincides with any one of P2, and the Y direction coincides with the other nozzle facing axis.

On the other hand, in the present embodiment, the thrust pattern is as shown by the symbol Q1 in FIG. 7, so that the phase angles 0, 90, 180 and 270 degrees are as follows. This means that a maximum efficiency of 100% (a thrust of 1) can be generated. For example, in order to generate the maximum thrust in the direction of 45 degrees at the phase angle, 1/2 gas is passed in the direction of 0 degree and 1/2 gas is passed in the direction of 90 degrees, so that 45 degrees is finally obtained. 0 in the direction of degrees.
It shows that a thrust of 865 can be generated. In the conventional case, in order to obtain the maximum thrust in the direction of 0 degree, 1/2 gas in the direction of 0 degree is used at 90 degrees and 27 degrees.
Since ¼ of the gas flows in the direction of 0 °, only 1/2 of the thrust can be generated in the direction of 0 °. However, in order to generate the maximum thrust in the direction of 45 degrees, 1/2 of each gas is flowed in the directions of 0 degree and 90 degrees, so that the thrust of 0.865 can be generated. As described above, the present embodiment has the advantage that the thrust pattern Q1 is dramatically larger than the conventional thrust pattern Q2.

In this embodiment, as shown in FIG. 8, the displacement of the cam 9 in the X direction is x, the displacement of the cam 9 in the Y direction is y, and the nozzles 4A to 4A. Set the opening area of the 4D throat section 7 to A1, B1, C
1, D1, the displacement x, y is proportional to the opening area A1, B1, C1, D1 of each nozzle throat, that is, the thrust force generated under the opening area A1, B1, C1, D1. In other words, in other words, in addition to the profile shape of the cam 9, the cam 9 and each pintle 8 are arranged so that the opening area of each nozzle throat portion 7 continuously changes as a function of the position of the pintle 8 which is the valve body. The relationship is predetermined. As a result, while keeping the total sum of the actual opening areas of the nozzle throat portions 7 always constant, at the same time, if necessary, only one of the nozzle throat portions 7 is fully opened and the other nozzle throat portions 7 are opened. By making it fully closed, it is possible to flow all the combustion gas from the gas generator side to one specific nozzle,
That is, the maximum sum of the actual opening areas of the nozzle throat portions 7 is set to be equal to the sum of the opening areas of the nozzle throat portions 7 for the total number of nozzles.

Therefore, according to the present embodiment, when the position in the rotational direction, which is the displacement x of the cam 9 in the X direction, is changed, for example, the thrust acting on the body 2 of the flying body 1 in the nozzle facing axis P1 direction. That is, the thrust difference based on the opening difference of the throat portion 7 between the two nozzles 4A and 4C on the nozzle facing axis P1 changes, and the thrust of this difference is applied to the body 2 of the flying vehicle 1 in the nozzle facing axis P1 direction. Acts as the thrust of.

At this time, with the rotational displacement of the cam 9, the thrust acting on the airframe 2 of the flying body 1 also changes at the same time in the other nozzle facing axis P2 direction, but as described above, the total number of nozzles is increased. The two nozzles 4B, 4 located on the other nozzle facing axis P2 so that the total sum of the actual opening areas of the throat portions of the minute is always constant.
Since the cam profile shape and the like are set in advance so that the thrust difference itself based on the opening difference between Ds does not change,
The net effective thrust does not change in the other nozzle facing axis P2 direction orthogonal to the nozzle facing axis P1 direction in which the thrust is positively controlled based on the rotational displacement of the cam 9.

Similarly, when the cam 9 is positively moved back and forth in the direction of the central axis C of the machine as the displacement y of the cam 9 in the Y direction, the thrust acting on the machine 2 of the flying body 1 in the direction of the nozzle facing axis P2. That is, the thrust difference based on the opening difference of the throat portion 7 between the two nozzles 4B and 4D on the nozzle facing axis P2 changes, and the thrust of this difference changes.
Will act on the machine body 2 as a thrust force in the direction of the nozzle facing axis P2.

Further, based on the opening characteristic of FIG. 8, by using the cam 9 in combination with rotation and forward / backward movement, one of the four nozzles 4A to 4D is fully opened as required. It is possible to fully close the three remaining nozzles. This means that the maximum thrust force based on the total sum of the opening areas of the throat portions corresponding to the total number of nozzles can be generated by one specific nozzle.

As described above, according to the present embodiment, the thrust pattern applied laterally to the body 2 of the flying vehicle 1 is dramatically increased even if the same amount of gas is generated, as compared with the conventional one. growing.

The servo motor 1 shown in FIGS.
The drive mode of the cam 9 by 1, 12 or the mechanism for rotating or reciprocating the cam 9 is only an example, and the point is that the rotation and the reciprocating movement of the cam 9 can be independently operated. Therefore, it goes without saying that another mechanism may be adopted.

9 to 11 show a second embodiment of the present invention, and the same parts as those of the first embodiment shown in FIGS. 1 to 4 are designated by the same reference numerals.

In the second embodiment, the structure of the flow control valve 21 is different from that of the first embodiment, and as shown in FIGS. 9 and 10, the chamber 3 functioning as a gas generator is used. Inside the single gas passage 22 connecting the nozzles 4 </ b> A to 4 </ b> D, there is provided a rotatable shutter 23 as a valve body that constitutes the flow rate control valve 21 together with the cam 9. Shutter 23
Is independent for each of the nozzles 4A to 4D, and opens and closes the throat portion 7 which is a flow rate adjusting port of each of the nozzles 4A to 4D. Each shutter 2
A shaft 24 is formed integrally with the shaft 3, and the shaft 3 is rotatably supported by a part of a partition wall 25 forming the gas passage 22. Also, each shutter 2
An arm 26 is integrally formed at the end of the cam 3, and the arm 26 projects to the outside of the gas passage 22. The edge of the tip of the arm 26 contacts the profile surface of the cam 9 as in FIGS. ing. The cam 9 is configured to be movable back and forth in the direction of the central axis C of the machine body and rotatable. The rotation of the cam 9 is performed by the servo motor 11, and the forward and backward movement of the cam 9 is performed by another servo motor 12. , Respectively, independently via the same mechanism as in FIGS.

Then, as shown in FIG. 11, each shutter 23 is rotationally displaced via the arm 26 in accordance with the rotational displacement or forward / backward movement of the cam 9, whereby the opening α of the nozzle throat portion 7, that is, the opening area is changed. It is controlled.

Here, also in the second embodiment, the profile shape of the cam 9 is changed so that the opening area of each nozzle throat portion 7 continuously changes as a function of the position of the shutter 23 which is the valve body. In addition, the relationship between the cam 9 and each arm 26 is determined in advance. As a result, while keeping the total sum of the actual opening areas of the nozzle throat portions 7 always constant, only one of the nozzle throat portions 7 is fully opened and the other nozzle throat portions are completely opened as needed. All the combustion gases from the gas generator side can be made to flow to one specific nozzle by closing the nozzles, that is, each nozzle throat portion 7
The maximum value of the total sum of the actual opening areas is set to be equal to the total sum of the areas of the nozzle throat portions 7 corresponding to the total number of nozzles.

Therefore, also in the second embodiment, the same operational effect as that of the first embodiment can be obtained.

FIG. 12 shows a third embodiment of the present invention, and the same parts as those of the first embodiment shown in FIGS. 1 to 4 are designated by the same reference numerals.

Also in this third embodiment, the structure of the flow control valve 31 is different from that of the first embodiment, and as shown in FIG. 12, the chamber 3 and each nozzle functioning as a gas generator are provided. A cylindrical orifice 33 that functions as a valve body of the flow rate control valve 31 is provided inside a single gas passage 32 that connects 4A to 4A and 4A to 4D. The orifice 33 is rotatable and movable back and forth in the central axis C of the machine body, and each nozzle 4A to 4D shares this single orifice 33, and each nozzle 4A to 4D.
Orifice passages 34 for opening / closing or adjusting the opening of the nozzle throat portion 7 are individually formed at positions corresponding to the nozzle throat portion 7 which is the flow rate adjusting port D.

In the orifice 33, an operating rod portion 35 formed integrally with the orifice 33 projects to the outside of the gas passage 32, and the operating rod portion 35 is rotatable via a bearing 36 and moves back and forth in the central axis C of the machine body. Supported as possible. The rotation of the orifice 33 is independently performed by the servo motor 11, and the forward / backward movement of the orifice 33 is independently performed by another servo motor 12 through the same mechanism as in FIGS. . This allows
By positively and variably adjusting the overlap amount (overlap amount) between each nozzle throat portion 7 and the orifice passage 34, each nozzle throat portion 7 is opened / closed or its opening degree is adjusted.

Here, also in the third embodiment, the servomotors 11 and 12 are arranged so that the opening area of each nozzle throat portion 7 continuously changes as a function of the position of the orifice 33 which is the valve body. The control characteristic of is determined in advance. As a result, while keeping the total sum of the actual opening areas of the nozzle throat portions 7 always constant, only one of the nozzle throat portions 7 is fully opened and the other nozzle throat portions are completely opened as needed. The closed state allows all the combustion gases from the gas generator side to flow to one specific nozzle, that is, the maximum sum of the actual opening area of each nozzle throat portion 7 is the total number of nozzles. It is set so as to be equivalent to the sum of the opening areas of the nozzle throat portion 7 for each minute.

FIG. 13 shows the nozzle throat section 7 shown in FIG.
FIG. 3 is a development explanatory view showing a mutual relationship between the nozzle throat portion and the orifice passage, and a portion where the nozzle throat portion 7 and the orifice passage 34 overlap each other, that is, a hatched portion is a nozzle throat portion. The effective opening area is 7. In the illustrated example, the opening degrees of the nozzle throat portions 7 are made equal to each other so that the total gas flow rate is 1%.
It shows a state in which each / 4 is made to flow to each nozzle throat portion 7.

Further, FIGS. 14A to 14C show another example of flow rate control. As shown in Table 1, FIG. 14A shows the total gas flow rate of the nozzle at the 0 ° phase position. 9/1 of gas flow rate
6, the nozzles at the 90-degree phase position and the 270-degree phase position have the same gas flow rate of 3/16, and the nozzles at the 180-degree phase position are opposed to the nozzle at the 0-degree phase position. The remaining 1/16
It was designed to flow the gas of. FIG. 12B
Shows that the gas flow rates of the nozzles at the 0-degree phase position and the 90-degree phase position are respectively halved, as shown in Table 2, and FIG. The total gas flow rate of the nozzle in the phase position is made to flow.

[0054]

[Table 1]

[0055]

[Table 2]

[0056]

[Table 3]

Here, although the flow rate of the nozzle at the 0 degree phase position in FIG. 9A is larger than 1/2 on 9/16 and the generated thrust is also larger than 1/2, it is opposed to 180. Since the flow rate of the nozzle at the 1-degree phase position is 1/16 and the corresponding thrust is generated, the generated thrust force corresponding to the gas flow rate of 1/16 is generated between the nozzle at the 0-degree phase position and the nozzle at the 180-degree phase position. Offsetting each other, resulting in a net effective thrust of 1/2 in the opposing axial directions of both nozzles.

Further, FIGS. 15 and 16 show that each nozzle throat portion 7 and the orifice passage 34 have a rhombic shape as shown in FIGS. 13 and 14, as is clear from comparison with FIGS. It goes without saying that the same functions as those described above are exhibited.

Therefore, also in the third embodiment, the same operational effects as those of the first embodiment can be obtained.

Here, in addition to the cam 9 in each of the above-described embodiments, the pintle 8 and the shutter 2 functioning as valve bodies.
Since 3 and the orifice 33 are exposed to the combustion gas, it is necessary to have sufficient heat resistance. Therefore, for example, zirconia is used as the material of the cam 9, and C / C composite (carbon / carbon composite), molybdenum, tungsten, SiC / SiC composite (silicon carbide / silicon carbide composite) is used as the material of the valve body. , C / SiC composite (carbon / silicon carbide composite), etc., either alone or in combination. Also,
A heat insulating layer such as aramid EPDM may be formed inside the surface layer such as tungsten that constitutes the valve body.
The heat resistance of each element is particularly advantageous in achieving long-time operation.

[Brief description of drawings]

FIG. 1 is a schematic explanatory view of an entire flying body including a side thruster.

FIG. 2 is a view showing the first embodiment of the present invention and is an enlarged sectional view taken along the line aa in FIG.

FIG. 3 is a sectional view taken along line bb of FIG.

FIG. 4 is a right side explanatory view of FIG. 3.

5 is an explanatory view showing a profile shape of the cam of FIGS.

FIG. 6 is an explanatory view of the profile shapes of the cams of FIGS. 2 and 3 viewed from different directions.

FIG. 7 is an explanatory diagram of a thrust pattern based on the opening characteristic of the nozzle throat portion of FIGS.

FIG. 8 is an explanatory diagram showing the opening characteristic of the nozzle throat portion of FIGS.

FIG. 9 is a view showing a second embodiment of the present invention and is a cross-sectional view of a portion equivalent to FIG.

10 is an enlarged cross-sectional view taken along the line dd of FIG.

FIG. 11 is an operation explanatory view of a main part of FIG.

FIG. 12 is a diagram showing a third embodiment of the present invention.
FIG.

FIG. 13 is a development explanatory view of a member forming a gas passage in FIG.

FIG. 14 is a development explanatory diagram showing another control pattern of FIG. 13;

FIG. 15 is a development explanatory view showing a modified example of the member of FIG.

16 is a development explanatory diagram showing another control pattern of FIG. 15. FIG.

[Explanation of symbols]

1 ... Flying body 2 ... Airframe 3 ... Chamber (gas generator) 4A to 4D ... Nozzle 6 ... Flow control valve 7 ... Nozzle throat (flow rate adjustment port) 8 ... Pintle (valve body) 9 ... cam 11, 12 ... Servo motor 21 ... Flow control valve 23 ... Shutter (valve body) 26 ... Arm 31 ... Flow control valve 33 ... Orifice (valve body) 34 ... Orifice passage C ... Airframe center axis P1, P2 ... Nozzle facing axis

Claims (8)

[Claims] 1. A plurality of nozzles that open toward the outer peripheral surface of the fuselage are arranged radially in a plane orthogonal to the fuselage center axis, and high-pressure gas is injected from any of the nozzles. This is a side thruster for a flying vehicle that generates thrust in a direction orthogonal to the center axis of the airframe to perform attitude control or trajectory control.While distributing high-pressure gas from the gas generator side to each nozzle, A flow control valve is provided to variably control the gas flow rate at the nozzle, and this flow control valve is designed to variably control the opening area of the flow control port of each nozzle as a function of the position of the valve body that opens and closes the flow control port. On the other hand, the total opening area of the flow adjustment ports for the total number of nozzles is set to always be a constant size. Side thrusters flying object, characterized by being adapted to be able to flow all the gas flow supplied from the gas generator side of the. 2. The valve element is independent for each nozzle, and each valve element is individually opened and closed by a single cam member shared by the plurality of valve elements. The side thruster for a flying vehicle according to claim 1. 3. Each nozzle shares a single valve body,
The side thruster for a flying vehicle according to claim 1, wherein the opening area of the flow rate adjusting port of each nozzle is individually and variably controlled by driving the valve body to open and close. 4. The flight according to claim 2, wherein the flow rate adjusting port is a throat portion of each nozzle, and the valve body variably controls an effective opening area of the nozzle throat portion. Body side thruster. 5. The valve body is a pintle that moves back and forth in the axial direction of the nozzle to open and close the nozzle throat, and each pintle is opened and closed by a rotatable cam member that can move forward and backward in the central axis direction of the machine body. The side thruster for a flying object according to claim 4, wherein 6. The valve body is a shutter rotatable about an axis parallel to the center axis of the machine body, and each shutter is opened / closed by a rotatable cam member that is movable in the axial direction of the machine body. The side thruster for a flying object according to claim 4, wherein 7. The valve body is an orifice which is arranged on the same axis as the central axis of the machine body and has an orifice passage corresponding to each nozzle throat part. The orifice is moved forward and backward in the central axis direction of the machine body. 5. The side thruster for a flying vehicle according to claim 4, wherein the amount of overlap between each orifice passage and the nozzle throat is variably controlled by rotationally driving. 8. The side thruster for a flying vehicle according to claim 2, wherein the valve body and the cam member are made of a heat resistant material.