FR2234465A1 - Cylindrical rocket propellant charge blocks - with central branched and eccentric axially directed channels - Google Patents
Cylindrical rocket propellant charge blocks - with central branched and eccentric axially directed channelsInfo
- Publication number
- FR2234465A1 FR2234465A1 FR7322275A FR7322275A FR2234465A1 FR 2234465 A1 FR2234465 A1 FR 2234465A1 FR 7322275 A FR7322275 A FR 7322275A FR 7322275 A FR7322275 A FR 7322275A FR 2234465 A1 FR2234465 A1 FR 2234465A1
- Authority
- FR
- France
- Prior art keywords
- block
- propellant charge
- rocket
- combustion
- partitions
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/10—Shape or structure of solid propellant charges
- F02K9/18—Shape or structure of solid propellant charges of the internal-burning type having a star or like shaped internal cavity
Abstract
Propellant block, esp. for rocket propulsion, with internal combustion, of cylindrical exterior comprising, in known manner, a peripheral ring with (n) distint partitions, each with two points of connexion to the ring, and a series of channels with walls parallel to the axis of the block and with a contour such as to provide a relative combustion thickness (e) e/r of 0.05-0.25, but in which the partitions delimit (i) a central branched channel enclosed between all the partitions and the outer ring and (ii) (n) eccentric channels each situated between one face of a single partition and the corresponding part of the peripheral ring, (where (e) is combustion thickness of the block and (R) the radius of the cylindrical block). Block gives an improved approach to the requirements for a rocket propellant charge i.e. (a) minimum variation of combustion surface to provide constant thrust throughout the rocket trajectory, (b) max. rates of propellant charge to volume occupied, and (c) min. unconsumed matl. in the period of normal rocket operation e.g. if the combustion surface has fallen to less than half.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR7322275A FR2234465A1 (en) | 1973-06-19 | 1973-06-19 | Cylindrical rocket propellant charge blocks - with central branched and eccentric axially directed channels |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR7322275A FR2234465A1 (en) | 1973-06-19 | 1973-06-19 | Cylindrical rocket propellant charge blocks - with central branched and eccentric axially directed channels |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| FR2234465A1 true FR2234465A1 (en) | 1975-01-17 |
| FR2234465B1 FR2234465B1 (en) | 1976-04-30 |
Family
ID=9121167
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| FR7322275A Granted FR2234465A1 (en) | 1973-06-19 | 1973-06-19 | Cylindrical rocket propellant charge blocks - with central branched and eccentric axially directed channels |
Country Status (1)
| Country | Link |
|---|---|
| FR (1) | FR2234465A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4714019A (en) * | 1985-07-18 | 1987-12-22 | Rheinmetall Gmbh | Inserts for coating an explosive charge, and forming a rod-shaped projectile, and process for manufacture of inserts |
| US20180112627A1 (en) * | 2015-08-07 | 2018-04-26 | Aerojet Rocketdyne, Inc. | Solid rocket motor with vortex inducing feature |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1068300A (en) * | 1952-12-12 | 1954-06-23 | Tubular powders with ribbed cavities | |
| FR1216901A (en) * | 1947-06-19 | 1960-04-29 | Soc Tech De Rech Ind | Improvements to propellant charges for jet engines |
-
1973
- 1973-06-19 FR FR7322275A patent/FR2234465A1/en active Granted
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1216901A (en) * | 1947-06-19 | 1960-04-29 | Soc Tech De Rech Ind | Improvements to propellant charges for jet engines |
| FR1068300A (en) * | 1952-12-12 | 1954-06-23 | Tubular powders with ribbed cavities |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4714019A (en) * | 1985-07-18 | 1987-12-22 | Rheinmetall Gmbh | Inserts for coating an explosive charge, and forming a rod-shaped projectile, and process for manufacture of inserts |
| US20180112627A1 (en) * | 2015-08-07 | 2018-04-26 | Aerojet Rocketdyne, Inc. | Solid rocket motor with vortex inducing feature |
| US10883448B2 (en) * | 2015-08-07 | 2021-01-05 | Aerojet Rocketdyne Inc. | Solid rocket motor with vortex inducing feature |
Also Published As
| Publication number | Publication date |
|---|---|
| FR2234465B1 (en) | 1976-04-30 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| ST | Notification of lapse |