JP3029960B2 - Extension nozzle mechanism of rocket engine - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to the use of a high expansion nozzle in a rocket engine having a high expansion nozzle with a large aperture ratio in order to operate with high efficiency in high air or space where ambient pressure is low. The present invention relates to an extension nozzle mechanism of a rocket engine which retracts and stores when not in use, and when used, extends the high expansion nozzle to a normal position and activates it.

[0002]

2. Description of the Related Art In order to efficiently operate a rocket launched from the ground in a high altitude space near a vacuum or in space, a rocket engine having a nozzle having a high expansion ratio needs to be provided. For this reason, liquid
Propellant tank consisting of oxygen tank, liquid hydrogen tank, etc.
After the lower (1st stage) rocket used to ascend from the ground to the high altitude using these propellants is separated, the upper (2nd stage) Rocket engines used for rocket propulsion and control have long lengths and have a problem in space for transferring them to the space where these rocket engines are operated. In order to solve this problem, a rocket engine comprising a nozzle expansion ratio, divided by the nozzle portion, the high expansion nozzle is a second half portion of the nozzle, Nozzle
Extruded forward to the periphery of the rocket engine with the remaining part, telescopically contracted like a telescope, transported with a small volume, and when activated, the high expansion nozzle extended backward and integrated with the nozzle part remaining in the rocket engine To be used as a rocket engine having a high expansion ratio.

Conventionally, the expansion of the high expansion nozzle is performed by driving a high expansion nozzle 01 in a state shown by a chain line in FIG. 8 by a screw jack or a piston driven by a driving device 02 such as a hydraulic, gas pressure, or electric motor. It is performed by moving the rocket engine 04, which is an operation position, to the rear of the rocket engine 04 by a moving device 03 such as an actuator so as to be in an operation state indicated by a solid line.

[0004] For this purpose, a power source (not shown) such as a hydraulic source, a gas source, and a power supply, a driving device 02 such as a hydraulic motor, a gas turbine, and an electric motor, and a moving device 03 such as an actuator such as a screw jack and a piston are provided. You need something heavy.

For this reason, not only does the launch capability of the rocket significantly deteriorate, but also these heavy objects cause the high-expansion nozzle to extend to the proper position, and the operating state for propulsion and control of the upper-stage rocket has been completed . Unless they are discarded later, they will sail with the upper rocket mounted as dead deadweights, losing the mounting capacity of the upper rocket, increasing the weight, and increasing the load on the upper rocket engine. There is a defect.

[0006]

SUMMARY OF THE INVENTION The present invention solves the above-mentioned problems of the conventional rocket engine, and enables a rocket engine which has been separated and transferred in a stowed state to be activated when a lower rocket is separated. It is an object to provide an extension nozzle mechanism for an engine.

[0007]

For this reason, the extension nozzle mechanism of the rocket engine of the present invention is characterized in that the separation of the lower rocket gives the lower rocket a momentum in a direction opposite to the traveling direction, so that the lower rocket is viewed from the upper rocket. Paying attention to the fact that it is dumped relatively rearward, the following means is adopted. (1) The propellant tank tip located at the tip of the lower rocket that is separated and dumped before the rocket engine starts operating
End outer surface (hereinafter simply referred to as the propellant tank tip
On the outer surface) . (2) From the retracted state to the operating state, the rear end of the high-expansion nozzle is provided at the rear end of the high-expansion nozzle with a fixed portion for coupling to the coupling device of the lower rocket with a constant holding force. (3) In order to bring the high expansion nozzle in the retracted state into the operating state, the coupling device and the fixed portion are connected to each other, and as the separated lower rocket moves rearward, the high expansion nozzle follows the rearward rocket. when moving, to generate a braking force in sliding contact with the outer periphery of the rocket engine on the inside, the connection between when the moving amount of the rear of the high expansion nozzle has reached a predetermined value, the coupling device and <br/> fixing portion the small diameter portion braking force exceed the force Ru is generated provided in the front end portion of the high expansion nozzle. (4) When the connection between the high-expansion nozzle moving rearward on the outer peripheral surface and the coupling device provided on the outer surface of the tip of the lower rocket propellant tank is released, the coupling surface coupled with the small-diameter portion of the high-expansion nozzle is removed. , provided at a rear end portion <br/> outer peripheral surface of the nozzle portion of the rocket engine rear. (5) A latch mechanism, which is coupled to the coupling surface and restricts the forward movement of the high expansion nozzle, is provided on the outer peripheral surface of the rear end of the nozzle portion.

Another rocket engine extension nozzle mechanism of the present invention employs the following means in addition to the above-mentioned means (1) to (5). (6) The coupling device is located outside the propellant tank tip of the lower rocket.
A support made of a flexible material, which is annularly disposed and fixed on the surface and whose peripheral edge portion can at least increase the sliding frictional force. The fixing portion was an inner peripheral surface at the rear end of the high expansion nozzle fitted to the peripheral edge of the support.

Another rocket engine extension nozzle mechanism of the present invention employs the following means in addition to the above-mentioned means (1) to (5). (7) The coupling device is located outside the propellant tank tip of the lower rocket.
A grooved support having a groove formed in a peripheral portion made of a flexible material, which is annularly disposed and fixed on the surface . In addition, the fixing portion fits into the groove of the grooved support, and the rear end periphery of the high expansion nozzle which receives a compressive force from both sides of the groove,
Outer peripheral surface.

Another rocket engine extension nozzle mechanism of the present invention employs the following means in addition to the above means (1) to (5). (8) The coupling device has one end coaxial and the propellant for the lower rocket
Two rods pivotally attached to the outer surface of the tank tip, a roller fixed to the other end of each rod, and a spring material interposed at the center of the two rods to apply a clamping force between the rods Scissors mechanism. Further, the fixing portion is fitted between the rollers to form an inner or outer peripheral surface of a rear end peripheral edge of the high expansion nozzle which receives a compressive force between the rollers by the spring material.

Another rocket engine extension nozzle mechanism of the present invention employs the following means in addition to the above-mentioned means (1) to (5). (9) One end of the coupling device is fixed to the outer surface of the front end of the propellant tank of the lower rocket. When a load exceeding the limit is applied to the central portion, the coupling device is cut from that portion and affects other portions. The bracket was cut into a notch so as not to cause damage. In addition, the fixing portion is a peripheral edge of the rear end of the high expansion nozzle to which the other end of the coupling bracket is fixed.

According to another aspect of the present invention, there is provided an extension nozzle mechanism for a rocket engine according to any one of the above (1) to (5) or (1).
To (6), the above (1) to (5), (7), the above (1) to (5), (8), or the above (1) to (5), ( The following means were used in addition to the means of 9). (10) At one of the rear end of the upper rocket or the tip of the lower rocket, a guide rail extends in parallel with the body axis of the upper rocket, and a traveling roller that runs along the guide rail is provided at the other end. Was.

[0013]

The extension nozzle mechanism of the rocket engine according to the present invention has the following features: (1) a rocket engine having a high expansion ratio, the upper end of which is connected to the rear end of the rocket engine; high expansion nozzle to form a is separated to move from a state of being stored around the rocket engine, rearward with lower rocket moves towards later by the disconnection of the upper rocket. At the rear of the rocket engine from which the high expansion nozzle is separated, a nozzle portion expanded rearward is left, and the small diameter portion provided at the tip of the high expansion nozzle is in sliding contact with the outer peripheral surface of this nozzle portion. However, as the nozzle diameter increases, the frictional force of the sliding contact part increases, and finally, the connecting force between the coupling device of the lower rocket and the fixed part of the high expansion nozzle exceeds, and the lower rocket The connection of the high expansion nozzle is released. On the outer peripheral surface of the nozzle at the position where this connection is released,
A connection surface is provided to connect the small diameter portion of the high expansion nozzle that has moved rearward.The connection between the lower rocket and the high expansion nozzle is released, and the rocket engine and the high expansion nozzle are connected. A rocket engine is formed.

Further, after the rocket engine and the high expansion nozzle are connected, the forward movement of the high expansion nozzle is restricted by the latch mechanism provided on the outer peripheral surface of the nozzle portion, and re-separation is prevented.

[0015] This eliminates the need for the heavy power source, power unit, and actuators required for the extension of the nozzle, which have caused the problems of the conventional device. Further, since the coupling device is discarded together with the lower rocket without the need for the coupling release mechanism, the problems of the conventional device can be solved without increasing the load on the upper rocket engine. In addition, the coupling device for connecting the high expansion nozzle to the lower rocket and the fixing portion can also serve as a mechanism for fixing and supporting the high expansion nozzle during operation of the lower rocket engine, so that an extra support mechanism is unnecessary. Becomes

Further, the extension nozzle mechanism of the rocket engine according to the present invention further includes the above-mentioned item (6) in addition to the function (1).
By means (2) by a frictional force between the inner peripheral surface and the unsupported peripheral edge of the rear end of the high expansion nozzle, can generate a coupling force between the moderate lower rocket and high expansion nozzle, high-expansion of a storage state A nozzle support mechanism is not required, and a special device for separation is not required. Further, since the coupling can be performed only by fitting the inner peripheral surface to the support, the weight can be reduced and the production becomes extremely easy. Further, by using a flexible material for the support, a frictional force capable of generating a predetermined coupling force can be obtained, and vibration generated when the lower rocket engine is operated can be suppressed from being transmitted to the high expansion nozzle.

Further, the extension nozzle mechanism of the rocket engine according to the present invention further includes the above-mentioned (7) in addition to the above-mentioned operation (1).
By means of (3), the bonding force between the grooved support and the inner peripheral surface of the rear end of the high expansion nozzle can be increased, and the high expansion nozzle can be reliably held in the stored state, and the same as ( 1 ) above. Perform the action.

Further, the extension nozzle mechanism of the rocket engine according to the present invention further includes the above-mentioned (8) in addition to the above-mentioned operation (1).
(4) The coupling force between the high expansion nozzle and the lower rocket can be freely controlled only by selecting the spring material. Further, it is not necessary to provide the fixing portion of the high expansion nozzle on the entire periphery of the rear end periphery, and the weight of the high expansion nozzle provided with the fixing portion can be reduced in addition to the weight reduction by the coupling device and the separation device.

Further, the extension nozzle mechanism of the rocket engine according to the present invention further includes the above-mentioned (9) in addition to the above-mentioned operation (1).
By means (5), the connection between the high expansion nozzle and the lower rocket can be simplified, the cost can be reduced, and the separation can be reliably performed with a predetermined load. Further, the weight of the high expansion nozzle can be reduced in the same manner as in the above (4).

Further, another extension nozzle mechanism of the rocket engine according to the present invention includes the above (1), (1), (2), (1), (3), (1), (4), Or (1),
In addition to the effect of (5), by means of (10) above, (6) the high expansion nozzle in the retracted state is
In accordance with the axial direction of the rocket engine, it can be accurately moved backward, preventing the small diameter part from hitting the outer peripheral surface of the nozzle part, and accurately guiding the high expansion nozzle to the connection position of the nozzle part, Can be combined. In addition, it is possible to prevent an accident in which the lower rocket after detachment contacts the high expansion nozzle or the like.

[0021]

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a perspective view of a rocket engine according to an embodiment of the present invention; FIG. 1 is a sectional view of a separation portion between an upper rocket and a lower rocket, and FIG.
1A is a cross-sectional view before separation, and FIG. 1B is a cross-sectional view at a certain point after separation.

As shown in FIG. 1A, the lower rocket 1
The upper rocket 2 and the upper rocket 2 are integrally connected by a connecting portion 3 having the same outer diameter, provided at the lower end of the lower rocket 1 (not shown), and arranged in a line in the axial direction of the lower rocket 1.
Inside a propellant tank consisting of a raw tank and a liquid oxygen tank
Launched to high altitude by a lower-stage rocket engine operated by a propellant . An upper rocket engine used in high altitudes where the pressure of the outer periphery is close to vacuum needs to have a high expansion ratio in order to be able to operate with high efficiency in high altitudes close to vacuum, and is very long, about 5 m. Also.

For this reason, the rocket engine 4 connected to the rear end of the upper stage rocket 2 and the high expansion nozzle 5 are separated by the nozzle portion 6, and the high expansion nozzle 5 is pushed out to the outer periphery of the front rocket engine 4, It is reduced to a length of about ／, is accommodated in an interstage defined between the rear end of the upper rocket 2 and the front end of the lower rocket 1, and is transported to a high altitude. As a result, the weight can be reduced by about 100 kg. The rear end of the high expansion nozzle 5 is located on the front end of the propellant tank disposed on the front end of the lower rocket 1.
Surface, a so-called annular ring fixed to the outer surface of the propellant tip ,
It is fitted and connected to a support 7 having a large coefficient of friction and serving as a cushioning material, which is made of a flexible material such as rubber. The support 7 has substantially the same shape as the outlet portion (rear end), which is the fixing portion of the high expansion nozzle 5, and has a truncated cone shape that is substantially larger than the inner surface shape of the rear end. The rear end of the expansion nozzle 5 is pressed into the support 7 and set.

When the combustion of the lower rocket engine is completed, the lower rocket 1 is cut off from the upper rocket 2 and discarded because it interferes with the mission. This dumping
The lower rocket 1 is given a momentum in a direction opposite to the traveling direction, and the lower rocket 1 is moved rearward. However, the high expansion nozzle 5 whose rear end is fitted into the support 7 and in a press-fit state is also provided. As shown in FIG. 1B, the vehicle retreats together with the lower rocket 1. The retraction of the high expansion nozzle 5 is performed by moving on the outer periphery of the rocket engine 4 and the nozzle portion 6 of the rocket engine 4 along the axis of the upper rocket 2 and the rocket engine 4. When the small-diameter portion 8 provided at the front end of the rocket engine 4 is retracted until it reaches a latch mechanism 15 described later provided on the outer peripheral surface of the nozzle portion 6 of the rocket engine 4 , the frictional force between the latch mechanism 15 and the small-diameter portion 8 causes Although the brake is applied to the reversing force, the lower rocket 1 continues to retreat further due to the large inertial force. At a position past the latch mechanism 15, the small diameter portion 8 slides on the coupling surface 11 having a larger diameter than the latch mechanism 15, and generates a frictional force larger than the coupling force connecting the high expansion nozzle 5 and the lower rocket 1. Then, the connection is released, and the high expansion nozzle 5 and the lower rocket 1 are separated.

[0025] As described above, the fixing portion is a rear end inner peripheral surface of the high expansion nozzle, propellant tanks tip out of the lower rocket
The connection with the support as a connecting device provided on the surface is dramatic in shape and is connected only by the connecting force by frictional force, so that the connection can be easily released. The high-expansion nozzle 5 is fixed in a state where the small-diameter portion 8 is in sliding contact with the coupling surface 11 provided on the nozzle portion 6 where this coupling is released.
Only the lower rocket 1 moves backward and is separated and dumped. As described above, since the operation of the lower rocket 1 that discards the high expansion nozzle 5 in the retracted state can be performed without requiring a power source, a power device, and a special moving device, the operation state can be reduced. A weight reduction of about 20 to 30 kg can be achieved.

Next, referring to FIG. 2, the latch mechanism 15 and the connection between the nozzle section 6 and the high expansion nozzle 5 will be described. A ring 10 is fixed to the entire outer periphery of the rear end of the nozzle portion 6, and a coupling surface 11 is formed on the outer periphery of the ring 10. Further, a latch mechanism 15 is provided in front of the ring 10 at equal intervals over the entire circumference of the nozzle portion 6. The latch mechanism 15 includes a hinge 12 installed on the outer peripheral surface of the nozzle portion 6 and a lever 1 mounted on the hinge 12.
3, a spring 14 interposed between the lower surface of the lever 13 and the outer peripheral surface of the nozzle portion 6 to apply an outward force to the lever 13, and a stopper 16 for preventing the lever 13 from jumping up.

As described above, the high expansion nozzle 5 connected to the lower rocket 1 retreats and moves while pressing the lever 13 inward on the inner wall surface of the small diameter portion 8 provided at the front end of the high expansion nozzle 5. When the movement is completed, the lever 13 is released, so that the lever 13 is again expanded outward by the force of the spring 14 and prevents the high expansion nozzle from moving in the reverse direction. Meanwhile, lever 1
The inner wall surface of the small-diameter portion 8 which has completed the movement on the upper surface 3 is suddenly brought into sliding contact with the inner surface of the ring 10 having a diameter larger than the diameter formed by the lever 13 when the spring 14 is pressed down. As a result, the coupling between the lower end of the high expansion nozzle and the front end of the lower rocket is released, and the small-diameter portion 8 remains in sliding contact with the coupling surface 11 and is coupled. Note that a sealing material 17 is applied in advance to the coupling surface, and leakage of gas between the coupling surface 11 and the small-diameter portion 8 is sealed by the sealing material 17.

Next, when the lower rocket 1 is separated, a guide device for accurately guiding the high expansion nozzle 5 retreating together with the lower rocket 1 in the axial direction of the rocket engine 4 will be described with reference to FIG.
This will be described below. Guide rails 18 are provided on the inner peripheral surface of the outer plate at the rear end of the upper rocket 2 in parallel with the body axis of the upper rocket 2.
Are provided at equal pitches in the circumferential direction toward the rear. On the other hand, on the inner peripheral surface of the outer plate at the front end of the lower rocket 1, a plurality of traveling rollers 19 traveling on the guide rails 18 are provided at positions corresponding to the guide rails 18 at intervals in the front and rear. Therefore, when the storage state of the high expansion nozzle 5 shown in FIG. 3A is changed to the operation state shown in FIG. 3B, the high expansion nozzle 5 is positioned at the axis of the upper rocket 2 (the axis of the rocket engine 3). And the position of the coupling surface 11 provided on the nozzle portion 6 and the small-diameter portion 8 can be accurately aligned without causing a twisting phenomenon. Of course, guide rail 1
8 may be provided at the front end of the lower rocket 1, and the running roller may be provided at the rear end of the upper rocket 2.

Next, FIG. 4 is a sectional view showing another embodiment of a support as a coupling device provided at the tip of the lower rocket 1. As shown in FIG. This support is the propellant for lower rocket 1 .
A main body 20 fixed to the outer surface of the tank tip;
The connecting portion 21 is formed by covering the peripheral portion of the cover with a flexible material. The shape and the operation are the same as those of the support 7 described above, but there is an advantage that the support 7 can be made lighter.

Next, FIG. 5 shows the conical surface support which is fitted to the fixed portion on the inner surface side of the high expansion nozzle in order to make the connection between the high expansion nozzle 5 and the lower rocket 1 more secure than that of the above embodiment. In addition to the high expansion nozzle 5, a groove 23 is formed on the outer surface side of the high expansion nozzle 5 by providing a buffer material 22 with an outer peripheral support on the entire circumference or partially on the circumference. This is a grooved support 24 that fits a fixing portion formed by the inner and outer peripheral surfaces of the end and supports it so as to sandwich it. In this embodiment, the grooved support 24 is used.
The cushioning material 22 with the outer peripheral support on the outer side of the above should not be completely pressed down with a conical surface, but be approximated to a cylindrical surface, or be foldable or have elasticity, so that the connection can be easily released. Is desirable.

FIG. 6 shows a roller 2 instead of the supports 7, 21 or the grooved support 24 in the above embodiment.
A scissor mechanism 25 provided with 6 facilitates connection and release between the high expansion nozzle 5 and the lower rocket 1. The scissor mechanism 25 is composed of two rods 2 whose base ends are pivotally coaxially mounted on the outer surface of the propellant tank of the lower rocket 1.
7, 27, rollers 26, 26 respectively provided at the distal ends of the rods 27, 27, and a spring member 28 which is interposed at the center of the rods 27, 27 and applies a clamping force between the rods 27, 27. Be composed.

The scissor mechanism 27 always presses and fixes a fixing portion provided at the rear end of the high expansion nozzle fitted between the rollers 26, 26 from the inner and outer surfaces by the spring force of the spring material 28 . When the lower rocket 1 is separated, the lower rocket 1 retreats. At this time, the high expansion nozzle 5 retreats together with the lower rocket 1 while being sandwiched by the scissor mechanism 25 to the normal position. When the high-expansion nozzle 5 is held at the normal position, only the lower rocket 1 moves backward. At this time, the high-expansion nozzle 5 is fixed by the rotation of the scissor mechanism 25 and the roller 26 and the movable mechanism of the rod 28. The part is separated rearward along the conical surface of the high expansion nozzle 5 while sandwiching the portion from inside and outside. With the scissor mechanism 25, not only can the detachment nozzle 5 and the lower rocket 1 be easily connected and released, but also the high expansion nozzle 5 can be easily connected to the nozzle portion 6.

Further, in this embodiment, the spring material 28
The coupling force can be freely set by the selection of, so that not only the supporting (holding) of the high expansion nozzle 5 in the stored state is reliably performed, but also the separation from the lower rocket 1 can be performed in an accurate state. In addition, it is not necessary to provide the fixing portion on the entire circumference of the rear end of the high expansion nozzle 5, and only the portion that fits into the roller 26 needs to be strengthened in strength, so that the weight of the high expansion nozzle 5 can be reduced.

Next, FIG. 7 shows the propellant tank of the lower rocket 1.
The outer surface of the tip of the rocket and the rear end of the high-expansion nozzle 5 are connected by a connecting bracket 29, and the lower rocket 1 is retracted. This is to be combined with the nozzle unit 6. The coupling bracket 29 is provided with a weak portion in strength so as to be separated from the weak portion. As a result, the lower rocket 1 and the high-expansion nozzle 5 can be connected with a simple mechanism, and the weight of the high-expansion nozzle can be reduced. Note that the coupling bracket 29 may be in the form of a wire.

[0035]

As described above in detail, according to the extension nozzle mechanism of the rocket engine of the present invention, a special power source for extending the stored high expansion nozzle is provided by the structure shown in the claims. Since no power unit and moving device are required, the structure is simple, the reliability is improved, and the weight can be reduced. In addition, there is no need for a special device to support the high expansion nozzle in the retracted state, which greatly contributes to the improvement of the launch capability of the rocket, and a coupling device that connects the high expansion nozzle and the lower rocket requires a special separation device. Without dumping, the rocket is dumped together with the lower rocket, so that the performance of the upper rocket can also be improved.

[Brief description of the drawings]

FIG. 1 is a view showing a separation portion of a lower rocket and an upper rocket, showing an embodiment of an extension nozzle mechanism of a rocket engine according to the present invention. FIG. 1 (A) is a side sectional view before separation, FIG.
(B) a side sectional view at the time when the high expansion nozzle is joined to the nozzle portion after separation,

FIG. 2 is a partial cross-sectional view showing a combined state of a rear end of a nozzle portion and a small diameter portion of a high expansion nozzle,

FIG. 3 is a view showing a guide device for guiding backward movement of the lower rocket and the high expansion nozzle when the lower rocket is separated, and FIG. 3 (A) is a side sectional view before separation;
(B) is a side sectional view at the time when the high expansion nozzle is joined to the nozzle portion after separation,

FIG. 4 is a partial sectional view showing a second embodiment of the coupling device and the fixing portion, and FIG. 4 (A) is a partial sectional view before separation.
(B) is a partial sectional view after separation,

FIG. 5 is a partial sectional view showing a third embodiment of the coupling device and the fixing portion, and FIG. 5 (A) is a partial sectional view before separation;
(B) is a partial sectional view after separation,

FIG. 6 is a partial sectional view showing a fourth embodiment of the coupling device and the fixing portion, and FIG. 6 (A) is a partial sectional view before separation;
(B) is a partial sectional view after separation,

FIG. 7 is a partial sectional view showing a fifth embodiment of the coupling device and the fixing portion, and FIG. 7A is a partial sectional view before separation;
(B) is a partial sectional view after separation.

FIG. 8 is a side sectional view showing an example of a conventional extension nozzle mechanism of a rocket engine.

[Explanation of symbols]

DESCRIPTION OF SYMBOLS 1 Lower rocket 2 Upper rocket 3 Coupling part 4 Rocket engine 5 High expansion nozzle 6 Nozzle part (with rocket engine) 7 Support 8 Small diameter part 10 Ring 11 Coupling surface 12 Hinge 13 Lever 14 Spring 15 Latch mechanism 16 Stopper 17 Seal material 18 Guide rail 19 Running roller 20 Main body 21 Connecting part 24 Grooved support 25 Scissor mechanism 26 Roller 27 Rod 28 Spring material 29 Connecting bracket

──────────────────────────────────────────────────続 き Continued on the front page (72) Inventor Masaaki Yasui 1200, Higashi Tanaka, Komaki City, Aichi Prefecture Mitsubishi Heavy Industries, Ltd. Nagoya Guidance and Propulsion System Works (56) References JP-A-48-83599 (JP, A) (58) ) Surveyed field (Int.Cl. ⁷ , DB name) F02K 9/76 F02K 9/97

Claims (6)

(57) [Claims] 1. A high-expansion nozzle having an end coupled to a rear end of a rocket engine is separated from the rocket engine and is loosely fitted around the rocket engine. estimation of the extension nozzle mechanism of the rocket engine to the operating conditions to be used in the promotion of the upper rocket, said lower stage rocket
A rocket engine having a coupling device disposed on the outer surface of the tip end of the fuel tank, a rocket engine having a nozzle connected to the rear end of the upper rocket and having a latch mechanism and a coupling surface provided on the outer peripheral surface of the rear end; A fixing portion connected to the coupling device in the retracted state is provided , and at the time of transition from the retracted state to the operating state at the front end portion, a sliding contact is made with the outer peripheral surface of the nozzle portion to release the coupling between the coupling device and the fixing portion. An extension nozzle mechanism for a rocket engine, comprising a high expansion nozzle provided with a small-diameter portion fitted to the coupling surface. Wherein said coupling device is estimated the lower rocket
An annular support fixed to the outer surface of the tip end of the fuel tank and having at least a peripheral portion formed of a flexible material, and the fixing portion is formed at a rear end of the high expansion nozzle fitted to the support. The extension nozzle mechanism for a rocket engine according to claim 1, wherein the inner peripheral surface is provided. Wherein the coupling device, estimation of the lower rocket
An annular grooved support fixed to the outer surface of the tip end of the fuel tank , formed of a flexible material, and having a groove formed in a peripheral portion thereof, wherein the fixing portion is fitted in the groove; 2. The extension nozzle mechanism for a rocket engine according to claim 1, wherein the extension nozzle mechanism is an outer peripheral surface of the rear end peripheral edge. Wherein said coupling device is estimated the lower rocket
A scissor mechanism including two rods, one end of which is coaxially pivotally mounted on the outer surface of the tip end of the fuel tank , rollers provided at the other end of the rod, and a spring material interposed at the center of the rod. The extension nozzle mechanism for a rocket engine according to claim 1, wherein the fixing portion is an outer peripheral surface of a rear end peripheral edge of the high expansion nozzle fitted between rollers of the scissor mechanism. 5. The thruster of the lower stage rocket according to claim 5, wherein
One end is fixed to the outer surface of the tip end of the fuel tank , and a connecting bracket is provided with a cutting notch in the center. The fixing portion is a rear end peripheral edge of a high expansion nozzle to which the other end of the connecting bracket is fixed. The extension nozzle mechanism for a rocket engine according to claim 1, wherein: 6. A guide rail provided at one of a rear end of the upper rocket and a front end of the lower rocket, the guide rail being disposed in parallel with a body axis of the rocket, and the other running on the guide rail. 6. The extension nozzle mechanism for a rocket engine according to claim 1, further comprising a roller.