JP5709259B2 - Pulse rocket motor - Google Patents

Description

  The present invention relates to a pulse rocket motor provided with a plurality of solid fuels.

The pulse rocket motor is configured by providing two or more propellants separated by a diaphragm or a partition in a single pressure vessel. This has an advantage that combustion at different timings can be realized in a solid fuel rocket that cannot be easily stopped and re-ignited.
Specifically, a propellant (first propellant) of pulse 1 (first pulse) is placed at the rear of the pressure vessel made of a carbon fiber / epoxy resin composition by the filament winding method, and a pulse is applied at the front. 2 (second pulse) propellant (second propellant) is provided, and a two-pulse rocket motor has been developed in which a barrier insulator (diaphragm) is disposed between these propellants (patent) Reference 1).

  In the two-pulse rocket motor of Patent Document 1, a front insulator is provided between the pressure vessel and the propellant for pulse 2, and a rear insulator is provided between the pressure vessel and the propellant for pulse 1 (first pulse). The front insulator, the rear insulator, and the barrier insulator are made of a synthetic rubber made of EPDM (ethylene / propylene / diene / monomer), and are partially overlapped and bonded to each other.

  As a manufacturing method of the two-pulse rocket motor of Patent Document 1, the two-pulse rocket motor is sequentially arranged from the front. Specifically, first, a front insulator is arranged on the inner surface of the pressure vessel, and the propellant for pulse 2 is applied. It is cast and cured under vacuum. Thereafter, a barrier insulator is attached to the propellant of the pulse 2 and the front insulator, and the front insulator is cut off. The rear insulator is then attached to the barrier insulator and a pulse 1 propellant (first propellant) is injected and cured. The inner surface of each of these insulators is coated with an adhesive liner, and is adhered to a corresponding propellant.

Japanese National Patent Publication No. 11-503802

  However, although the pressure vessel of the above-mentioned Patent Document 1 is formed by directly forming the carbon fiber / epoxy resin composition around the propellant by the filament winding method, the pressure vessel made of resin is made of metal. Due to the manufacturing method in which the pressure vessel is molded directly around the propellant in this way, the front insulator, the rear insulator, and the barrier insulator are each coated with an adhesive liner and propelled. There is a problem that a process for bonding with a medicine is required, and the manufacturing process is complicated.

Furthermore, the barrier insulator that partitions the propellant of pulse 1 and pulse 2 needs to prevent the intrusion of flame into the propellant of pulse 2 during the combustion of the propellant of pulse 1, but the barrier insulator and the front insulator There is a possibility that the bonded portion of the film may be peeled off due to deterioration over time, and there is a possibility that the intrusion of the flame cannot be surely prevented.
On the other hand, the barrier insulator needs to be broken at a predetermined position and not fall off at the time of pulse 2 propellant combustion so as not to fall off and clog the nozzle. On the other hand, in Patent Document 1, it is assumed that the front insulator and the barrier insulator are broken at the bonding portion, but the setting of the breaking strength by bonding is complicated, and breaks at an appropriate timing. Is not easy. Further, as described above, since each insulator is bonded to the propellant, it acts to prevent the barrier insulator from being peeled off from the propellant at the time of pulse 2 propellant ignition, and there is a problem from the viewpoint of reliable operation. is there.

  Further, in Patent Document 1, a propellant support (foaming material or the like) is provided around the central throat portion of the front insulator, and the periphery is covered so that the front insulator is wrapped around. Since the propellant support is less rigid than the propellant, the portion of the front insulator that covers the propellant support is deformed by the combustion pressure of pulse 1 and stress is concentrated. There is. Thus, when the insulator of the propellant support portion is deformed, there arises a problem that the reliability of the operation of the pulse 2 is lowered.

  The present invention has been made to solve such a problem, and the object of the present invention is to prevent a flame from entering the second propellant during the first pulse with a simple configuration and to ensure that It is to provide a pulse rocket motor capable of executing the second pulse.

  In order to achieve the above object, in the pulse rocket motor according to claim 1, a hollow cylindrical first propellant provided at a subsequent stage in the pressure vessel, a first igniter for igniting the first propellant, A hollow cylindrical second propellant provided in the previous stage in the pressure vessel, a second igniter for igniting the second propellant, and between the second igniter and the second propellant, A propellant support provided on the front side and the axial center side of the second propellant, and a diaphragm member that covers the second propellant in the pressure vessel, the diaphragm member being the second propellant The diaphragm extends along at least the inner peripheral surface of the first and second ends of the diaphragm and is integrated by vulcanization adhesion, and has a holding tool attached to the pressure vessel.

The pulse rocket motor according to claim 2 is the pulse rocket motor according to claim 1, wherein the holder on the front end side of the diaphragm of the holder has a vulcanized adhesion portion with the diaphragm facing rearward at least over the range of the propellant support. It is characterized by a convex cross section extending.
The pulse rocket motor according to a third aspect is characterized in that, in the first or second aspect, the diaphragm of the diaphragm member is formed with a weakened part weaker than other parts.

  In the pulse rocket motor according to claim 4, in claim 3, the diaphragm is bent from the inner peripheral surface of the second propellant along the rear end surface, and the weakened portion is formed around the bent portion. It is characterized by being.

  According to the present invention using the above means, in the pulse rocket motor, the second propellant is covered in the pressure vessel for the purpose of preventing the flame from entering the second propellant during the combustion of the first propellant, and the diaphragm Is extended along at least the inner peripheral surface of the second propellant, and the diaphragm member is firmly bonded to the holder by chemical bonding by vulcanization adhesion, and the diaphragm is integrated from the holder to the diaphragm. Since the second propellant is covered by the configuration, there is no risk of peeling of the adhesive due to deterioration over time, and it is possible to reliably prevent the flame from entering the second propellant at the time of the first pulse.

In addition, since the diaphragm member is attached to the pressure vessel by a holder that is integral with the diaphragm, it is not necessary to bond the diaphragm to the propellant, and manufacturing is facilitated, and the propellant and the diaphragm are bonded. When the second propellant is ignited (second pulse), the diaphragm is easily peeled off from the second propellant, and the second pulse can be operated reliably.
Further, the holder on the front end side of the diaphragm has a vulcanized adhesion portion with the diaphragm extending rearward at least over the range of the propellant support, so that the first pulse (at the time of first propellant combustion) The combustion pressure is received by a metal holding member. Therefore, the strength of the propellant support portion in the diaphragm member can be ensured, and deformation or breakage of the portion can be prevented.

  From the above, it is possible to reliably prevent the intrusion of flame into the second propellant at the time of the first pulse and operate the second pulse with a simple configuration.

1 is an overall configuration cross-sectional view of a pulse rocket motor according to an embodiment of the present invention. It is a principal part expanded sectional view of FIG. It is a partially cutaway perspective view of a diaphragm member. FIG. 3 is an enlarged front sectional view of FIG. 2. FIG. 3 is an enlarged rear sectional view of FIG. 2. It is an operation | movement figure of the pulse rocket motor which concerns on this invention.

Hereinafter, embodiments of the present invention will be described with reference to the drawings.
Referring to FIGS. 1 to 5, FIG. 1 is a cross-sectional view of an entire configuration of a pulse rocket motor according to an embodiment of the present invention, FIG. 2 is an enlarged cross-sectional view of a main part, and FIG. 4 is a front enlarged sectional view of FIG. 2, and FIG. 5 is a rear enlarged sectional view of FIG.
A two-pulse rocket motor 1 shown in FIG. 1 is provided with a nozzle 4 at the rear of the pressure vessel 2, in which a first propellant 6, which is a solid fuel, is located at the rear, and a second propellant 8 is located at the front. The second propellant 8 is covered with the diaphragm member 10. In addition, a first igniter 12 for igniting the first propellant 6 and a second igniter 14 for igniting the second propellant 8 are provided at the front portion of the pressure vessel 2.

  Specifically, the pressure vessel 2 is a two-part metal motor case, and is configured by a front case 2a and a rear case 2b having a substantially cylindrical shape having the same diameter and connected to each other on the same axis. In the front case 2a and the rear case 2b, the rear end opening edge of the front case 2a and the front end opening edge of the rear case 2b are fastened by a plurality of bolts. As the material of the pressure vessel 2, titanium, maraging steel, D6AC steel, chrome molybdenum steel or the like is preferably used. Further, the outer periphery of the pressure vessel 2 is covered with an external insulator 16.

  The first propellant 6 is a propellant for the first pulse that burns first, and has a hollow cylindrical shape extending in the front-rear direction. The first propellant 6 is provided in the rear case 2 b via a rear heat insulating material 18. From the center in the front-rear direction of the first propellant 6, the cross section of the inner hole forms a star shape to increase the combustion area, and the inner hole communicates with the outside through the inside of the nozzle 4. The first propellant 6 is a composite propellant. In addition, the inner hole of the first propellant may have a circular cross section throughout, or a light beam cross section such as a star shape may be formed at an arbitrary position such as rearward from the center in the front-rear direction.

  The second propellant 8 is a propellant for the second pulse that burns later, and has a hollow cylindrical shape extending in the front-rear direction. As shown in detail in FIG. 2, the second propellant 8 is provided in the front case 2 a via a front heat insulating material 20. The cross section of the inner hole of the second propellant 8 is circular, and communicates with the inner hole of the first propellant 6 via the diaphragm member 10. The second propellant 8 is a composite propellant.

Moreover, the axial center side part of the front part of the 2nd propellant 8 is notched in the convex cone shape to the back, and the propellant support body 22 is provided so that the said notch part may be filled up. The propellant support 22 has a lower density than the second propellant 8 and is a flammable material, such as a foam material.
In the diaphragm member 10, a diaphragm 24 made of EPDM rubber having heat insulation properties is attached to the pressure vessel 2 via diaphragm holding metal fittings 26a and 26b (holding tools) provided at both ends.

  As shown in FIGS. 2 and 3, the diaphragm 24 is inclined rearwardly from the rear end of the inner surface portion 24 a and the inner surface portion 24 a extending in the front-rear direction along the inner peripheral surface of the inner hole of the second propellant 8. However, it has a substantially funnel shape composed of an end surface portion 24b that expands radially outward. Further, the diaphragm 24 is formed as a fragile portion 24c in which a bent portion from the inner surface portion 24a to the end surface portion 24b is structurally weaker than other portions. The weakened portion 24c is set in advance so as to break when subjected to a combustion pressure of a predetermined value or more.

  The diaphragm holding metal fittings 26a and 26b are respectively formed in an annular shape, and are spaced along the circumferential direction on the front surface of the diaphragm holding metal fitting 26a on the front end side and on the outer peripheral surface of the diaphragm holding metal fitting 26b on the rear end side. A plurality of bolt holes 28a, 28b are formed. The diaphragm member 10 is attached to the pressure vessel 2 by being fastened with bolts that are screwed into the bolt holes 28a and 28b. The diaphragm holding metal fittings 26a and 26b are preferably made of metal in terms of airtightness and heat resistance, but may be a holder made of FRP or the like as long as they have similar airtightness and heat resistance.

Here, the attachment structure of the diaphragm 24 and the diaphragm holding metal fittings 26a and 26b will be described in more detail with reference to FIGS.
As shown in FIG. 4, the diaphragm holding metal fitting 26a on the front end side is formed with a convex portion 30a having a convex cross section reduced toward the rear on the annular rear surface. And the said convex part 30a has entered into the front-end part of the inner surface part 24a of the diaphragm extended in the front-back direction, and the said convex part 30a and the inner surface part 24a of the diaphragm are united by vulcanization adhesion. In addition, the front end side diaphragm holding metal fitting 26 a has the front end of the convex portion 30 a coincident with the rear end of the propellant support 22 in the front-rear direction, and the convex portion 30 a extends over the range of the propellant support 22. It extends.

  On the other hand, as shown in FIG. 5, the diaphragm holding metal fitting 26b on the rear end side is formed with a convex portion 30b having a convex cross-section that is reduced inward on the annular inner surface. And the said convex part 30b has penetrated into the rear-end part of the end surface part 24b of the diaphragm extended in radial direction, and the said convex part 30b and the end surface part 24b of the diaphragm are united by vulcanization adhesion. And the said end surface part 24b is directly contacting with the 1st propellant 6 and the 2nd propellant 8, and has divided both.

  Referring again to FIG. 2, the first igniter 12 is attached to the axial center portion of the partition wall 2 c that closes the front portion of the pressure vessel 2, and is inside the inner hole of the second propellant 8, that is, the inner surface portion 24 a of the diaphragm member 10. It protrudes toward the rear. A plurality of ignition holes 32 extending to the propellant support 22 are formed in the partition wall 2c with different phases, and the second igniter 14 is connected to the plurality of ignition holes 32. The second igniter 14 has a ring-shaped cavity, and is filled with an igniting agent. When the second pulse is ignited, the toroidal igniter has a function of propagating the flame of the igniting agent to all the ignition holes 32. It is.

The operation of the thus-configured pulse rocket motor according to the present invention will be described below.
FIG. 6 shows operation diagrams (a) to (d) of the pulse rocket motor according to the present invention, which will be described below. In addition, the pulse rocket motor of FIG. 6 has simplified and shown the pulse rocket motor of the said FIGS.
FIG. 6A shows the state of the first pulse. When the first igniter 12 is ignited, the combustion of the first propellant 6 is started. Combustion occurs from the inner peripheral surface of the inner hole of the first propellant 6, and the combustion gas F1 is injected into the atmosphere through the nozzle 4. As a result, the two-pulse rocket motor 1 obtains the propulsive force by the first pulse.

  At this time, the second propellant 8 is covered with the diaphragm member 10 which is integrated with the diaphragm holding metal fittings 26a and 26b at both ends and reaches the diaphragm 24, so that the ignition flame of the first igniter 12 and the first propulsion The combustion gas F1 of the medicine 6 does not enter. In particular, a propellant support 22 having a lower rigidity than the second propellant 8 is provided at the front axial center portion of the second propellant 8, but the diaphragm is closer to the axial center than the propellant support 22. Since the projection 30a of the diaphragm holding metal fitting 26a at the front end of the member 10 extends, the pressure received from the combustion gas F1 is received by the metal diaphragm holding metal fitting 26a having sufficient strength, and the diaphragm member 10 is not deformed. Absent.

And as shown in FIG.6 (b), a 1st pulse is complete | finished when all the 1st propellants 6 finish burning.
FIG. 6C shows the state of the second pulse. When the second igniter 14 is ignited at an arbitrary timing, an ignition fire reaches the propellant support 22 through the ignition hole 32, and the propellant support 22 first burns. In response to the combustion of the propellant support 22, the second propellant 8 burns from the inner surface toward the rear end surface, and a combustion gas F <b> 2 is generated between the inner surface of the second propellant 8 and the partition member 10. In response to this combustion pressure, the diaphragm 24 expands with respect to the second propellant 8 and deforms inward of the pressure vessel 2.

  As shown in FIG. 6D, when the deformation of the diaphragm 24 proceeds, the diaphragm 24 breaks at the weakened portion 24c that is more fragile than the other portions. After the fracture, the combustion gas F2 is injected into the atmosphere through the nozzle 4, so that the combustion gas F2 causes the inner surface 24a of the diaphragm 24 to buckle axially and the end surface 24b curves backward. . The inner surface portion 24a and the end surface portion 24b of the diaphragm 24 are burned down by the combustion gas F2, but a certain amount of non-burning layer is maintained so that the strength of the diaphragm 24 necessary to prevent harmful separation of the diaphragm 24 can be maintained. Since the thickness of the diaphragm 24 is designed so as to leave the above, the second pulse ends when all of the second propellant 8 is burned without causing a harmful dropout such as clogging the nozzle 4.

  As described above, in the two-pulse rocket motor 1 according to the present embodiment, the diaphragm member 10 has the diaphragm 24 firmly bonded to the diaphragm holders 26a and 26b by chemical bonding by vulcanization bonding, and the diaphragm holder 26a, Since the second propellant 8 is covered in an integrated configuration from 26b to the diaphragm 24, there is no risk of peeling of the adhesive due to deterioration over time, and the flame of the second propellant 8 at the time of the first pulse Intrusion can be reliably prevented.

  Further, since the diaphragm member 10 is attached to the pressure vessel 2 by the diaphragm holders 26a and 26b that are integrated with the diaphragm 24, it is not necessary to adhere the diaphragm 24 to the propellants 6 and 8, and the manufacture is easy. In addition, since the propellants 6 and 8 and the diaphragm 24 are not adhered, the diaphragm 24 is easily peeled off from the second propellant 8 during the second pulse, and the second pulse can be executed reliably.

Further, the diaphragm holder 26a on the front end side has a convex portion 30a, which is a vulcanized adhesion portion with the diaphragm 24, extending rearward at least over the range of the propellant support 22 so that the first pulse time can be reduced. The combustion pressure is received by the metal diaphragm holder 26a. Therefore, the strength of the propellant support 22 portion in the diaphragm member 10 can be secured, and deformation or breakage of the portion can be prevented.
Further, the weakened portion 24c that is weaker than the other portions is formed in the bent portion from the inner surface portion 24a to the end surface portion 24b in the diaphragm 24, so that a combustion pressure equal to or higher than a predetermined value preliminarily assumed at the time of the second pulse can be obtained. If it receives, it will fracture | rupture reliably in the said weak part 24c. Thus, in the weak part 24c provided in the diaphragm 24 of the part which covers the 2nd propellant 8, when the diaphragm 24 isolate | separates reliably, the diaphragm 24 may fall out and clog the nozzle 4. Further, the separated diaphragm 24 does not block the combustion gas F2 from the second propellant 8. In addition, the weak part 24c of the diaphragm 24 can be provided not only in the bending part from the inner surface part 24a to the end surface part 24b but in the arbitrary places of the diaphragm 24.

In this way, the two-pulse rocket motor 1 according to the present embodiment has a simple configuration and reliably prevents the flame from entering the second propellant 8 during the first pulse, and reliably executes the second pulse. be able to.
Although the description of the embodiment of the pulse rocket motor according to the present invention is finished as above, the embodiment is not limited to the above embodiment.

The loading amounts and the like of the first propellant 6 and the second propellant 8 are not limited to those shown in the above embodiment, and are appropriately set according to the application. For example, the first propellant may have a hollow cylindrical shape throughout, or a cylindrical shape including a light cross section.
Moreover, although the pressure vessel 2 of the said embodiment was a 2 division system, this invention is applicable also to an integrated pressure vessel without division.

  Moreover, in the said embodiment, although the diaphragm 24 is extended over the end surface part 24b from the inner peripheral part 24a of the 2nd propellant 8, the said diaphragm 24 is along the inner peripheral part 24a of the 2nd propellant 8 at least. It only has to extend to cover the second propellant 8. For example, when the inner wall which divides a 1st propellant and a 2nd propellant is formed in the pressure vessel, it is set as the diaphragm of only the inner surface part extended along the internal peripheral surface of a 2nd propellant. And the diaphragm holding metal fittings are provided at both ends of the diaphragm, the diaphragm holding metal fitting on the front end side is the partition wall in the front part of the pressure vessel, and the diaphragm holding metal fitting on the rear end side is the inner wall that partitions the first propellant and the second propellant. It shall be attached to each.

DESCRIPTION OF SYMBOLS 1 2 pulse rocket motor 2 Pressure vessel 4 Nozzle 6 1st propellant 8 2nd propellant 10 Diaphragm member 12 1st igniter 14 2nd igniter 22 Propellant support body 24 Diaphragm 24a Inner surface part 24b End surface part 24c Fragile part 26a, 26b Diaphragm holding bracket (holding tool)
30a, 30b Convex part

Claims (4)

A hollow cylindrical first propellant provided at a subsequent stage in the pressure vessel;
A first igniter for igniting the first propellant;
A hollow cylindrical second propellant provided in the previous stage in the pressure vessel;
A second igniter for igniting the second propellant;
A propellant support provided between the second igniter and the second propellant and provided on the front side and the axial side of the second propellant;
A diaphragm member covering the second propellant in the pressure vessel,
The diaphragm member has a diaphragm extending along at least an inner peripheral surface of the second propellant, and is integrated by vulcanization adhesion at both ends of the diaphragm, and has a holder attached to the pressure vessel. A pulse rocket motor characterized by   Of the holders, the holder at the front end side of the diaphragm has a convex cross-section in which a vulcanized adhesive portion with the diaphragm extends rearward and extends at least over the range of the propellant support. The pulse rocket motor according to claim 1.   3. The pulse rocket motor according to claim 1, wherein the diaphragm of the diaphragm member is formed with a weakened part weaker than other parts in a part thereof.   4. The pulse rocket motor according to claim 3, wherein the diaphragm is bent from an inner peripheral surface of the second propellant along a rear end surface, and the weakened portion is formed around the bent portion. 5. .