JP3510527B2 - Lateral thrust control device - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION [0001] BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a flying object
The control device used for control, especially the airframe in a direction orthogonal to the airframe axis
High pressure gas is injected from the position of the center of gravity.
Lateral movement without changing the attitude angle in the direction perpendicular to the aircraft axis
Or from a position away from the center of gravity
To generate a rotational moment around the center of gravity of the machine.
Or eccentric from the direction perpendicular to the fuselage axis.
Injects pressurized gas to generate a rotational moment about the axis
And these flying moments cause the attitude of the flying object
A lateral thrust control device that controls motion by changing the angle
Related. [0002] [Prior Art] Motion control of a flying object flying at high speed
As a rule, the rotating body around the weight of the flying body
And the direction of the fuselage axis is changed.
Rotational moments around the center of gravity, such as pitch angle control and yaw angle control
Motion control using the
Is performed by tilting the aircraft from the horizontal direction
Utilization of rotational moment about axis center such as roll angle control
Motion control, and rotation around the machine weight center or axis center
The direction of the fuselage axis can be
Move the aircraft up and down or left and right while
There is a movement control that is performed without generating a statement. [0003] In addition, for controlling these movements,
The control device moves at high speed around the outside of the flying object.
Control device of the steering wing type that makes use of the aerodynamic force
Or from the thrust engine installed at the rear end of the flying object
By changing the direction of the injected gas that is injected backward at high speed,
Use the reaction force of deflected injection gas (thrust)
There are vane type controls. However, a control device of the steering wing type,
Drive system that drives the control device, etc.
Structure becomes complicated, and especially the steering wing or vane
It is necessary to install a drive device to rotate these
Is required to increase the weight and complicate the structure.
Point, and changes due to the rotation of the steering blade or vane.
Changes in the moving air or jet gas flow
Therefore, the control force required for motion control is generated for the first time.
In addition, there is a disadvantage that the control response becomes poor. For this reason, weight reduction and high exercise performance are required.
Flying vehicles have high temperatures in a direction perpendicular to the fuselage axis.
High-pressure gas such as the combustion gas of
The aircraft is moved in a direction perpendicular to the fuselage axis by the
Cause the so-called aircraft to move laterally,
Inject high-pressure gas in a direction eccentric from the orthogonal direction,
A flying object that generates a rotational moment around the aircraft axis
To control the motion by changing the posture angle of
The position of this jet gas in the machine axis direction away from the center of gravity of the machine
The aircraft is powered by the reaction force of the propellant gas
A rotational moment around the center of gravity is generated,
The attitude angle of the flying object by the dynamic or rotational moment
Adopts a lateral thrust control device that changes the motion control
There are things that I try to do. FIG. 3 is a sectional view of a conventional lateral thrust control device.
FIG. 3A shows a lateral thrust control device.
For cutting the flying object at the axial position where the nozzle is mounted
FIG. 3B shows a cross-sectional view of FIG.
A longitudinal section in which the circumferential position in the direction of arrow AA is cut in the axial direction.
FIG. [0007] In the lateral thrust control device shown in FIG.
Consists of two nozzles 02 arranged opposite to each other
A control mechanism constituting one set of the lateral thrust control device 015 has two
A pair of transverse thrust control devices that are orthogonally arranged and opposed to each other
Controls lateral thrusts in two directions generated in opposite directions with the installation 015
And control the lateral thrust in all four directions as a whole.
You. As shown in FIG.
Is a nozzle 02 screwed to the manifold 01,
The axis of the nozzle 02 is aligned with the axis of the
Piston head 0 inserted into hole 09 drilled in
10 and a poppet portion 011 in contact with the opening of the nozzle 02
Nozzle control valve 03 provided with
Pie connected to the rear end face side of the
It consists of a lot valve 04. The lateral thrust control device 015 has a nozzle
Working medium that generates lateral thrust by jetting from the opening of 02
Generation for generating and supplying combustion gas G
Propellant-filled chamber 06, part of the vessel, propulsion
Chamber 08, which burns the agent to generate high-temperature gas, combustion chamber
08 to accelerate the high-temperature gas generated in each nozzle 02
A throat 07 for injecting into the branching chamber is provided.
At the same time, the manifold 01
The combustion gas G generated by these gas generators is
When the poppet unit 011 is opened by the operation of the control valve 03,
Introduce into the gas reservoir 012 for guiding to the opening of the nozzle 02
Gas passage 05 is formed. Next, FIG. 4 shows the nozzle control valve 03 shown in FIG.
Of the gas reservoir 012 through the gas flow path 05
To supply the combustion gas G introduced through the nozzle 02 to the nozzle 02
FIG. 4A is a diagram schematically showing the operation of FIG.
The poppet part 011 formed at the tip of the valve 03 is a nozzle
02 was installed in the opening that opened to the gas reservoir 012
The opening is closed by contacting the valve seat and the nozzle 02
FIG. 3 is a diagram showing a state in which the injection of the combustion gas G is not performed;
FIG. 4B shows the poppet part 011 opened apart from the valve seat.
Is opened by the nozzle control valve 03 and the nozzle 0
2 is injected to the outside of the combustion gas G,
The state in which the control device 015 is activated to generate the lateral thrust F
FIG. That is, the gas generator shown in FIG.
The combustion gas G generated in the combustion chamber 08 constituting
Pass through the throat 07, which constitutes the gas generator, to the branch room
Gas flow path 05 which is introduced, branched and communicates with each nozzle 02
The combustion gas G flowing into the gas passage and passing through the gas passage 05
Side where the poppet part 011 side of the control valve 03 is arranged
The gas is introduced into the gas reservoir 012 defined in FIG. Also figure
As shown in FIG. 4, the combustion gas G is introduced and P₁pressure
In the room on the poppet part 011 side of the nozzle control valve 03
A certain gas reservoir 012 is connected to a piston of the nozzle control valve 03.
To the piston working chamber 013 formed behind the
Area S₁Through the orifice 014
The inside of the stone working chamber 013 flows through the orifice 014.
Pressure P due to the incoming combustion gas G_TwoIt has become. Further, the pressure P_TwoBecomes the piston working chamber 01
3 is S when fully open_TwoFormed on the pilot valve cross section
A pilot valve 04 for opening and closing the opening (hereinafter, the description will be simplified)
The pilot valve cross-sectional area to S_TwoShall be called
You. ) To open air. This pie
Lot valve cross section S_TwoIs drilled in the piston head 010
Orifice cross section S of orifice 014₁Bigger
Therefore, as shown in FIG.
When the cut valve 04 is fully opened, the pressure in the piston working chamber 013 is
Force P_TwoIs the pressure P of the gas reservoir 012₁Lower than. [0013] The conventional lateral thrust control device 015 is as described above.
The electric control pilot valve 04
Is excited, as shown in FIG.
013 is the pilot valve cross-sectional area S_TwoPilot of
Closed by the valve 04, the inside of the gas reservoir 012 and the piston working chamber
013 is connected to orifice 014
And gas reservoir pressure P₁And piston working chamber pressure P_TwoWhat is
Gas reservoir pressure P₁Acting piston
The area of the front end face of the head 010 is the piston working chamber pressure P
_TwoFrom the area of the rear end face of the piston head 010
Is small, the nozzle control valve 03 is connected to the poppet unit 011.
Into contact with the valve seat installed in the opening of the nozzle 02
As shown in FIG. 4 (a), close the chil 02
It moves upward toward the opening of the nozzle 02. [0014] Thus, the outside through the opening of the nozzle 02
Since there is no combustion gas G flow injected into the nozzle, the nozzle 0
In No. 2, the lateral thrust F cannot be generated. Also, the electrically controlled pilot valve 04 is de-energized.
When magnetized, the piston head 010 is large from the rear end face side.
The opening of the flow passage communicating with the air has a pilot valve cross-sectional area S_TwoNo pa
The piston working chamber 013 is opened by the pilot valve 04,
Pilot valve cross-sectional area S_TwoThe opening of the pipe communicates with the atmosphere
The combustion gas G in the ton working chamber 013 is released to the atmosphere. Moreover, the orifice cross-sectional area S₁Is Pylo
G valve cross-sectional area S_TwoThe combustion gas G
Is restricted by the orifice 014, and the gas reservoir pressure P
₁Is the piston working chamber pressure P_TwoBigger than
As described above, the gas reservoir pressure P₁To the working piston
The pressure receiving area of the pad 010 is equal to the piston working chamber pressure P._TwoIs made
Smaller than the pressure receiving area of the piston head 010 used
Nevertheless, as shown in FIG.
Is a poppet 0 in contact with the valve seat at the opening of the nozzle 02.
11 is retracted to open the opening of the nozzle 02 as shown in FIG.
It moves downward as shown in (b). As a result, the fuel in the opening in the nozzle 02
The combustion gas G flows, and the combustion gas G
By the injection, a lateral thrust F is generated at the nozzle 02. When such a lateral thrust F is generated,
Nozzle 02 for stopping generation of thrust F, nozzle control valve
03, pilot valve 04 is opposed to up, down and left and right
Lateral thrust control unit 015
And always keep the flow path of the combustion gas G closed.
So that one of them is always open
This prevents abnormal pressure rise in the gas generator
In such a way as to prevent the occurrence of abnormal combustion in the combustion chamber 08.
I have to. However, such a conventional lateral thrust system
The control device 015 has the following problems.
It has become something. (1) The opening of the nozzle 02 is P₁> P_Two
"Fully open" when the nozzle control valve 03 moves to the bottom
Or P₁= P_TwoOf the piston head 010
The nozzle control valve 03 moves to the top due to the difference in pressure receiving area
Operation can only be performed in either of the "fully closed" states.
The opening of the mouth cannot be controlled continuously,
Therefore, subtle movement control of the flying object is not possible. (2) Subtle flying object motion control
Pie that opens and closes with a motor that can be controlled continuously
Nozzle control by continuous opening control of lot valve 04
Hold valve 03 in the middle position between the lowermost position and the uppermost position.
It is considered that the pilot valve 04 is connected to the gas reservoir 012
Through the orifice 014 from the piston working chamber 01
3 to be exposed to the high temperature combustion gas G
To stabilize the operation of pilot valve 04.
Control of the flying object
The performance that can be achieved by controlling the operation of
Difficult to do. (3) Due to an abnormality in the control system, all pyro
There is a possibility that the shut-off valve 04 may be closed.
In such a case, all nozzles 02 are fully closed and the gas generator
The combustion gas G generated in the above is not discharged to the outside at all,
The pressure inside the generator rises abnormally and the gas generator explodes
Possibilities arise and there are safety issues. (4) The nozzle 02 is controlled to be fully open and fully closed.
Can not be fully opened and fully closed or fully closed and fully open
The degree of opening can be changed continuously at a constant speed slowly
Can not control the opening degree of the transient nozzle 02
Therefore, the total opening area for discharging the combustion gas G to the outside
Changes, this also results in a sudden increase in the combustion pressure of the gas generator.
And may cause abnormal combustion in the combustion chamber 08.
And the combustion efficiency is reduced and a large amount of lateral thrust F is generated.
Need propellants. The lateral thrust control device is described above.
In addition to the lateral thrust control device 015, two pilot valves
Some are operated individually instead of operating in pairs
is there. However, with such a lateral thrust control device,
Has four pilot valves in addition to the above-mentioned problems.
Four control circuits are required to control each independently
And the nozzle control valve 03 is driven.
To increase the driving force of each pilot valve 04
There is a problem that the installation of the device is required. [0025] SUMMARY OF THE INVENTION The present invention provides
Conventional lateral thrust control device, especially to operate in pairs
To generate lateral thrust by installing a nozzle control valve
Nozzle to prevent the malfunction of the lateral thrust control unit
The opening of the mouth can be controlled continuously, and the nozzle opening can be controlled continuously.
If you can do subtle movement control of the flying object by changing it
In both cases, the total opening area for discharging the combustion gas G to the outside is sudden
It can be prevented from changing drastically, and the combustion pressure of the gas generator suddenly increases.
The combustion in the combustion chamber 08 caused by the drastic change
It is possible to make efficient combustion without causing
The amount of propellant for generating the lateral thrust F can be reduced.
In order to control the nozzle control valve,
Through the orifice and into the piston working chamber
Exposed to hot combustion gas G
Eliminates the need to use an pilot valve,
The operation performance can be stabilized and the nozzle can be opened continuously.
Performs subtle flying object motion control in conjunction with degree control
Can be controlled by the
The possibility of the nozzle control valve being closed is eliminated,
The pressure inside the gas generator rises abnormally, causing the gas generator to explode
Can be avoided and there are no safety issues
To provide a lateral thrust control device capable of
And [0026] SUMMARY OF THE INVENTION For this reason, the present invention is not limited thereto.
The force control device was as follows. (1) Arranged to face the axis of the flying object
Installed and formed on each of two nozzles
High-pressure gas with a different flow rate from the opening
Fly between nozzles that generate transverse forces in orthogonal directions.
The axial direction is arranged in a direction passing through the axis of the body and orthogonal to the axis.
AndIn addition, it can slide in its own axis center direction by rod guide
Noh,For each of the two opposing nozzles
And a rod that can be moved forward and backward. The rod is positioned with respect to the axis of the flying object.
Each set of nozzles provided facing each other
High pressure gas is injected from only one nozzle and the other
Move the nozzle control valve to a position where it is not ejected from the nozzle
As well as the position of the nozzle control valve.
The flow rate of the high-pressure gas injected from each nozzle
It can be held in a position that can be made at any ratio
preferable. In addition, a nozzle provided opposite to the axis is provided.
Slurs are made up of two or more sets in addition to one set
It is good. (2) Each rod is connected to both ends.
Forward and backward toward the openings formed in each of the nozzles
Along with the rod to move in the axial direction,
Toward the opening formed in each of the nozzlesYou
ToWith poppet,Poppet section provided at the nozzle opening
The distance between the valve seat and the
By changing the area of the opening where the compressed gas is injected,
A type that can change the magnitude of the lateral thrust generated by
A slip control valve is provided. Note that the nozzle control valve for injecting the high-pressure gas is
The area of the opening increases and decreases in the axial direction.
Nozzle control valve that changes according to the amount of rod
Nozzle so that the total opening area is constant regardless of the position
The distance between the poppet at the tip of the control valve and the opening is adjusted.
Preferably. (3) Poppet provided at the tip of nozzle control valve
Change the distance between the slot and the nozzle opening to inject high-pressure gas.
The lateral thrust generated by the nozzle by changing the area of the opening
Point the nozzle control valve to the opening to change the size of
Driving means for moving the rod for moving forward and backward in the axial direction
Was provided. The driving means is the axis of the flying object.
Is provided at a position deviated from the forward and backward directions of the rod,
An eccentric shaft fitted in a slot provided in the rod;
It includes a drive shaft coupled to an eccentric shaft,
The rod is moved back and forth along its axis.
If high temperature combustion gas is used as
Is provided at a distance from the gas flow path that supplies the nozzles.
To avoid direct contact of the combustion gases, for example,
The flow path is provided on the outer peripheral side of the fuselage where the nozzle is
A drive means is installed on the inner circumference of the road to prevent it from getting hot
It is preferable that the operation does not become unstable.(4) Lateral force in the direction perpendicular to the axis by injecting high pressure gas
Is generated in the same position in the axial direction of the flying object
Are arranged at an angle of 90 ° in the circumferential direction.
And the two placed opposite the axis of the flying object
Nozzle with two sets of nozzles consisting of two nozzles
It consisted of (5) Point the nozzle control valve at the two nozzle openings
A rod that moves forward and backward to change the area of the nozzle opening
Pass through the axis of the flying object,
It consists of two rods arranged in
In order to freely move in and out of the axis independently of the
One of the rods
Penetrate and one rod penetrates the other
The length required for the full stroke of the other rod
Shall be provided with a long hole and one rod shall be penetrated.
Was. The lateral thrust control device according to the present invention has the above (1) to
(3), And (4), (5)By means of (A) The rod can slide in the axial direction by the rod guide
In the axial direction of the rod by the driving means.
The nozzle control valve is accurately and reliably directed toward the opening by moving back and forth.
By moving back and forth, the nozzle opening can be fully open or fully closed.
Not only in any state, but also in the middle between fully open and fully closed
The opening can be controlled to a continuous opening degree.
The rod moves in the axial direction, in other words, the opening
To the opening of the nozzle control valve to control the opening
High-temperature combustion gas is in direct contact with the drive means
The nozzle control valve opening
The opening control of the section can be made more stable,
You can make the body perform subtle exercise control,
Excellent performance can be achieved. Driving means for driving the nozzle control valve;
Or an error has occurred in the control system for controlling this
In all cases, the total opening of the nozzle opening area is always
By keeping it constant, all nozzle openings
Abnormal pressure rise in the gas generator due to clogging
To avoid gas generator explosion, etc.
And eliminate the associated safety issues.
Possible, and abnormal combustion due to pressure rise in the gas generator
To prevent lateral propulsion
Reduction of propellants and the like can be measured. Further, the total opening degree of the nozzle opening area is always constant.
To minimize the change in the total opening.
To a set of nozzle control valves connected to both ends of the rod
Offsets the drive load that drives the rod against the acting pressure
Driving force required by the driving means
Can be reduced. The nozzle control valve is connected to both ends of the rod.
One set of two nozzle control valves is shared by one drive means.
To control the nozzle control valve.
Control circuit can be halved and the nozzle control valve
The driving force required to move
Installation of an amplifier, etc. to amplify the driving force of the
It becomes unnecessary. [0037] [0038] [0039] [0040]Further, In addition to the above (a), (B) Upper, lower and left and right lateral thrusts of the flying object
A lateral thrust control device that can generate
The flying object has better athletic performance and is more accurate
Can also do flying that can do subtle exercise
Can be In addition, two rods pass through the shaft center,
AlsoSo that the two rods can move independently of each other
AndOne of the two rods is
Penetrate the long hole provided in the other rod, and
The two sets of nozzles are
It can be operated independently and has two additional nozzles
The four nozzles formed are the same position in the axial direction of the flying object.
That are activated by the two rods
The injection of high pressure gas by the spill control valve allows
Generate up, down, left and right lateral thrusts at the same position
Will be able to Also, the four nozzles are located at the center of the flying object.
Are located at the same position in the same direction.
The lateral thrust generated is the same in the axial direction of the flying object.
Lateral thrust generated at each position and generated by two sets of nozzles
The rotational moment generated around the center of gravity by the force
The same rotation mode is obtained by the lateral thrust generated by
And fly without changing the attitude angle.
When moving the body up, down and left and right
What happens depending on the set of nozzles that are activated
There is no rotational moment around the center of gravity
So let's fly without any change in attitude angle
Can be. [0043] DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, a lateral thrust control device according to the present invention will be described.
An embodiment will be described with reference to the drawings. FIG. 1 shows an embodiment of a lateral thrust control device according to the present invention.
FIG. 1A is a cross-sectional view showing a first embodiment, and FIG.
Next to the flying object at the axial position with
FIG. 1B is a cross-sectional view, and FIG.
Shows a vertical cross-section of the flying object near
are doing. It should be noted that the members shown in FIGS.
Similar members are denoted by the same reference numerals and description thereof is omitted.
You. As shown in FIG. 1, the lateral thrust of the present embodiment
The control device 15 is connected to the manifold 01 by screws and
Nozzle 02 arranged so as to face, opening of nozzle 02
Poppet part 0 in chalk part (throat part) 16
11 is inserted into the gas reservoir 01 of the choke 16.
2 The distance between the valve seat provided at the opening and the poppet part 011
Nozzle system to determine the opening of the choke part 16
Control valve 03, two nozzle control valves 03 provided facing each other
Mechanically connecting rod 17, this rod 17
Rod guide 1 that slidably holds in the axial direction of 17
8, a slot 19 forming a part of the rod 17 and
A drive shaft 21 having an eccentric shaft 20 to be fitted,
Bearings 22 and 23 for rotatably holding shaft 21, drive
A stepping motor 24 controls the rotation of the shaft 21.
You. As described above, the rod 17 is moved forward and backward.
The driving means includes a stepping motor 24, a driving shaft 21 and
And an eccentric shaft 20 fitted in the slot 19.
You. The lateral thrust control device 15 according to the present embodiment
Now, the operating mechanism of the two sets of nozzle control valves 03 having the above configuration
Structures are orthogonally arranged on the same plane, and one set of nozzles
The axial direction of the rod 17 for mechanically connecting the control valve 03
Make a long hole, so-called cavity,
The other pair of nozzle control valves 03 is mechanically connected.
Rod 17 is passed through this cavity,
The rods 17 are arranged at the same position in the axial direction, and
It can be driven upright. By doing so, the axis of the flying object
To generate lateral thrusts in two opposite directions.
Nozzle control valve 03 is connected to both ends, and a set of nozzles
The rod 17 that forms the chisel 02 is orthogonally
Can be arranged, and two orthogonally arranged
The rod 17 can be operated on a plane having the same axial direction.
And prevents the generation of axial moment components.
I'm here. Further, the gas reservoir 0
12 and the nozzle 0 is opened and closed by opening and closing the nozzle control valve 03.
Gas generator that generates lateral thrust by injecting it from the outside to the outside
A chamber 06 filled with a solid propellant,
Combustion of body propellant to generate combustion gas G as high pressure gas
Combustion chamber 08 to be generated and combustion generated in combustion chamber 08
The throat 07 for injecting the gas G into the gas flow path 05 is shown in FIG.
It is provided similarly. Next, the lateral thrust control device 15 of this embodiment
Now, an operating device for operating the nozzle control valve 03 will be described.
I will tell. FIG. 2 is a simulation showing the operation of the lateral thrust control device.
FIG. 2 (a) shows the neutral state of the actuator, that is,
Combustion discharged to the outside from the nozzle 02 arranged in the opposite direction
FIG. 2B shows a state in which the flow rates of the gas G are balanced.
The actuating device is in working condition, i.e.
Flow rate of the combustion gas G discharged from the nozzle 02
It becomes unbalanced and discharges from the right nozzle 02 shown in the figure to the outside.
The flow rate of the discharged combustion gas G increases, and the nozzle 02 on the opposite side
The flow rate of the combustion gas G discharged from the
It is a figure which shows the operation state which is generating the lateral thrust on the right side. As shown in FIG.
The distance between the valve 03 and the valve seat provided on the choke part 16
Stepping mode set to neutral
The motor 24 rotates around the drive shaft 21 and rotates clockwise.
Then, the eccentric shaft 20 integrally formed therewith also swings clockwise.
Move. The swing of the eccentric shaft 20 is substantially equivalent to that of the rod 17.
It is transmitted to the slot 19 formed in the center and the rod 17
Slide to the left. The movement of the rod 17 in the axial direction is
Of the nozzle control valve 03 mechanically connected to both ends of the
Between the pet part 011 and the valve seat that the poppet part 011 contacts
By changing the interval, it is formed by the gap between the poppet part 011 and the valve seat.
Opening of the choke 16 as the opening of the nozzle 02
Change the area. The nozzle system is provided with the nozzle 02 provided facing the nozzle.
The opening area formed between the control valve 03 and the valve
When the door 17 slides to the left, the left nozzle 02
The area of the opening formed between the nozzle control valve 03 and
Between the nozzle 02 on the right and the nozzle control valve 03
As the area of the opening formed increases, one increases
Then the other decreases by the same amount and this increase or
The change in the area of the opening, which decreases, is caused by the stepping motor 2
4 will depend on the rotation angle. Therefore, the gas generator passes through the gas passage 05.
The combustion gas G supplied to the gas reservoir 012 is
02 and the nozzle control valve 03, more precisely the poppet unit 011
The opening formed by the horizontal movement of the rod 17 between the valve seats
Generates thrust to the right by squirting from nozzle 02 through the mouth
This thrust causes the nozzle 02 to move the center of gravity of the flying object.
If the flying object is installed in
Move it to the left side on the opposite side, and move nozzle 02
If it is located further back, move the flying object to the center of gravity.
Instead, it generates a turning moment that rotates counterclockwise.
And change the attitude angle of the flying object. The rotation direction of the stepping motor 24
When it is turned counterclockwise, it is formed at substantially the center of the rod 17.
The eccentric shaft 20 inserted into the slot 19
Direction around the drive shaft 21 in the direction
The rotational force of the rod 24 is to slide the rod 17 to the right.
To the nozzle 19 on the right side.
Nozzle control that moves to the right by moving the door 17 to the right
The area of the opening formed with the valve 03 is reduced,
Opening formed between the nozzle 02 and the nozzle control valve 03
The area of the mouth is enlarged, and the stepping motor 24 described above is used.
As in the case of the clockwise rotation of
(Left opening area) increases depending on the rotation angle of
Then the other (the opening area on the right) decreases by that much
To reverse the direction of thrust to generate thrust to the left,
Move the flying object to the right or clock around the center of gravity
Generate a rotational moment to rotate in the direction. As described above, the lateral thrust according to the present embodiment is
Since the control device is configured as described above, (1) Nozzle 02 is either “fully open” or “fully closed”
Rather than continuous actuation, continuous opening between full open and fully closed
The combustion gas injected from the nozzle 02 can be controlled.
By changing the injection amount of the gas and changing the magnitude of the lateral thrust continuously.
Subtle movement control of the body can be performed,
The exercise performance of the housing can be improved. (2) The opening of the nozzle that generates thrust
Need for fine control of nozzle control valve to control strangely
The motor that operates is a high-temperature combustion gas like a conventional pilot valve.
Control of the nozzle control valve
Subtle thrust by controlling the nozzle opening
Becomes possible. This enables continuous opening control of the nozzle
In combination with this, it is possible to perform subtle flight object motion control.
Can improve the flying body's athletic performance.
Wear. (3) Due to an abnormality in the control system, all nozzles
The possibility of a closed control valve is eliminated and
Even if an abnormality occurs, the nozzle associated with the operation of the nozzle control valve
The total area of the openings in the gas generator is always kept constant.
Pressure may rise abnormally and the gas generator may explode.
Performance and avoid safety issues.
And can. (4) The total opening area of the transient nozzle is one
The total opening area changes rapidly
The gas generator combustion pressure that could occur
Because there is no rapid change, combustion in the combustion chamber 08
To cause efficient combustion without causing abnormalities
And the amount of propellant can be reduced. (5) A pair of control valves are connected by a rod,
Drive the rod with an actuator, etc.
Open the opening of the spill and minimize the change in the total opening area
So that one end is mechanically connected to both ends of the rod.
The drive load against the pressure acting on the set of nozzle control valves.
To minimize the driving force of the actuator.
can do. (6) A pair of nozzle control valves are mechanically
And connected to both ends of the rod for synchronous control.
Control circuit for controlling each of the nozzle control valves.
Path can be at least halved and the driving force of the nozzle control valve is reduced.
Installation of an amplifying device can be eliminated. [0063] As described above, the lateral thrust system according to the present invention is
The control device is installed opposite to the axis of the flying object.
Different from the opening formed in the two nozzles paired
Lateral force in the direction perpendicular to the axis by injecting high-pressure gas at a flow rate
Between the nozzles that generate
Two nozzles that are slidably held in their own axial direction.
Rod that can move forward and backward, and both ends of the rod
Respectively, and move back and forth toward the nozzle opening
With the rod moving in the axial direction, it retreats toward the opening,
Change the distance between the tip and the opening to inject high-pressure gas.
Change the area of the opening that is used to increase the lateral thrust generated by the nozzle.
Nozzle control valve with variable size and nozzle control valve
Change the space between the valve and the nozzle opening to increase the area of the opening.
To change the amount of lateral thrust generated by the nozzle
Move the rod that moves the nozzle control valve toward the opening
Driving means for moving forward and backward, and the driving means
Is the direction of the rod's advance and retreat from the axis of the flying object.
A slot portion provided in the rod, provided in a biased position;
The eccentric shaft fitted to the eccentric shaft and the drive shaft
Including and configuringIn addition, the high pressure gas is injected,
Nozzle that generates lateral force in the direction perpendicular to
90 ° angle in the circumferential direction at the same position in the body axis direction
From the two nozzles
Two sets of nozzles are provided, and the nozzle control valve
Forward and backward toward the nozzle opening to reduce the area of the nozzle opening.
Changing rods are arranged perpendicular to each other through the axis
Two rods, and the two rods
So that they can move independently, for example, to the other rod
One rod does not hinder and the other rod moves back and forth
To provide a long hole necessary for
By passing the other rod through the slot
Both rods can be freely moved in the axial direction. The lateral thrust control device of the present invention thereby
Nozzle control by axial movement of rod by moving means
The valve faces the openingAccurate and reliableRetract and open the nozzle
The part can be controlled to a continuous opening between fully open and fully closed.
Nozzle control by moving the rod back and forth in the axial direction
The driving means for moving back and forth toward the valve opening
It can be arranged not to be affected by gas,
Opening control can be made more stable,
The body can be made to have excellent exercise performance. Driving means for driving the nozzle control valve;
Or, if an abnormality occurs in the control system,
The total opening of the area is always kept constant and the opening is closed.
Abnormal pressure rise in the gas generator caused by
Without explosion, etc.
Can eliminate the problem and furthermore the pressure in the gas generator
Abnormal combustion due to the rise can be prevented, and the amount of propellant etc. is reduced.
Can be Further, the total opening degree of the nozzle opening area is always constant.
Act on the nozzle control valve
The drive load that resists pressure can be offset,
The driving force required for the step can be reduced. A nozzle for controlling two nozzles in one set
The control valve can be driven synchronously by one drive means,
Control circuits can be halved and driving power can be reduced.
An amplifier for amplifying the driving force of the nozzle control valve
Installation is not required. [0068] [0069]Furthermore,Up, down and left and right directions of the flying object
Lateral thrust control device that can freely generate lateral thrust
The two rods pass through the shaft center and
So that the two rods can move independently of each other,
For example, one of the two rods
Through the long hole provided in the other rod, the two rods
Axial movement is free, and two sets of nozzles operate independently.
As well as two sets of nozzles
Four nozzles are arranged at the same position in the axial direction,
The injection of high-pressure gas by the sloW control valve allows the axial
One side can generate up, down and left and right lateral thrusts.
And the four nozzles are at the same position in the axial direction.
Lateral thrust generated by two sets of nozzles
Occur at the same position in the axial direction, so two sets of nozzles
Rotation around the center of gravity due to lateral thrust generated by
Is controlled by the lateral thrust generated by either set of nozzles.
Can have the same rotational moment and change the attitude angle.
Fly up, down and left and right
Change the attitude angle regardless of the set of nozzles to be activated.
A flying object with no aging is created, and the flying object has athletic performance
Can be further improved.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a cross-sectional view showing a first embodiment of a lateral thrust control device of the present invention, and FIG. 1 (a) is a shaft on which the lateral thrust control device of the present embodiment is mounted. FIG. 1 (b) is a longitudinal sectional view in which the vicinity of an axial position where a lateral thrust control device is mounted is cut in the axial direction, and FIG. FIG. 2A is a schematic cross-sectional view showing the operation of the lateral thrust control device of FIG.
FIG. 3B is a diagram showing an operating state; FIG. 3 is a sectional view showing a conventional lateral thrust control device;
FIG. 3A is a cross-sectional view of the flying object taken at the axial position where the lateral thrust control device is mounted, and FIG.
FIG. 4A is a longitudinal sectional view taken in the axial direction of the vicinity of the axial position where the lateral thrust control device is mounted in the direction of arrows AA shown in FIG. 4A; FIG. 4 is a simulation showing the operation of the lateral thrust control device shown in FIG. FIG. 4A is a sectional view showing the nozzle in an open state, and FIG.
(B) is a diagram showing a nozzle closed state. [Description of Signs] 01 Manifold 02 Nozzle 03 Nozzle control valve 04 Pilot valve 05 Gas flow path 06 Chamber 07 Throat 08 Combustion chamber 09 Hole 010 Piston head 011 Poppet section 012 Gas storage section 013 Piston working chamber 014 Orifice 15,015 Lateral thrust Control device 16 Choke part 17 Rod 18 Rod guide 19 Slot 20 Eccentric shaft 21 Drive shaft 22, 23 Bearing 24 Stepping motor G Combustion gas F Lateral thrust S ₁ Orifice cross-sectional area S ₂ Pilot valve cross-sectional area P ₁ Gas reservoir pressure P ₂ Piston working chamber pressure

────────────────────────────────────────────────── ─── Continuation of the front page (56) References JP-A-11-83396 (JP, A) JP-A-10-103156 (JP, A) JP-A-8-74664 (JP, A) JP-A-59-1983 192851 (JP, A) JP-A-54-9499 (JP, A) (58) Fields investigated (Int. Cl. ⁷ , DB name) F42B 10/66

Claims (1)

(57) [Claims 1] A pair of nozzles provided to be opposed to the axis of a flying object is disposed, and is directed toward an opening formed in each of the nozzles. In a lateral thrust control device that advances and retreats a nozzle control valve to change the area of the opening, injects high-pressure gas of a different flow rate from the nozzle, and generates a lateral force in a direction orthogonal to the axis on the flying object. A rod that passes through the axis orthogonal to the axis and is arranged in the axial direction in the direction of the opening, is disposed between the opposing openings, and moves toward and away from the opening; The nozzle control valve is connected to both ends of the rod, moves forward and backward toward the opening with the advance and retreat of the rod, and changes the area of the opening, and driving means for moving the rod forward and backward is provided. By guide The driving means is provided at a position deviated from the axis of the flying object in the advance / retreat direction of the rod, and is fitted in a slot provided in the rod. An eccentric shaft and a drive shaft coupled to the eccentric shaft , wherein the nozzle is provided with a 90 ° circumferential angle and
It is located at the same position in the axis direction and faces the axis.
The nozzle consists of two sets
The rods for moving the control valves forward and backward respectively correspond to the shaft center.
Through two rods that are
The two rods can move independently of each other.
Thus, one of the rods is located at the shaft center and the other
And each of the rods
To be able to move back and forth toward the opening provided in
Horizontal thrust control apparatus characterized by there.