JP2721138B2 - Solid fuel rocket combustion chamber shape - Google Patents
Solid fuel rocket combustion chamber shapeInfo
- Publication number
- JP2721138B2 JP2721138B2 JP7243528A JP24352895A JP2721138B2 JP 2721138 B2 JP2721138 B2 JP 2721138B2 JP 7243528 A JP7243528 A JP 7243528A JP 24352895 A JP24352895 A JP 24352895A JP 2721138 B2 JP2721138 B2 JP 2721138B2
- Authority
- JP
- Japan
- Prior art keywords
- combustion chamber
- solid fuel
- fuel rocket
- rocket
- shape
- 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.)
- Expired - Lifetime
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/403—Solid propellant rocket engines
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/002—Launch systems
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Solid Fuels And Fuel-Associated Substances (AREA)
Description
【０００１】[0001]
【産業上の利用分野】本発明は固体燃料ロケットの燃焼
室において燃焼力の向上を促進し進力を増強しロケット
の速度をより速くするための固体燃料ロケットの燃焼室
の形状に係わる発明である。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to the shape of a solid fuel rocket combustion chamber for promoting the improvement of combustion power in a combustion chamber of a solid fuel rocket, enhancing the advance and increasing the speed of the rocket. is there.
【０００２】[0002]
【従来の技術】従来・固体燃料ロケット燃焼室の形状は
第３図、第４図及び第５図、第６図に示した様に、内部
に縦溝を設ける加工・製作がなされそれなりの進力を発
生して来たが少々物足りない進力であった。BACKGROUND ART shape prior-solid fuel rocket combustion chamber Figure 3, Figure 4 and Figure 5, as shown in Figure 6, the internal
The advance force of its own way is gunna processed and manufactured providing a longitudinal groove came occurs but was a little unsatisfactory advance force.
【０００３】[0003]
【発明が解決しようとする課題】従来の固体燃料ロケッ
トの燃焼室の形状は、第３図、第４図及び第５図、第６
図の形の物で有ったが固体燃料には、酸化剤が含まれて
いる為燃料の燃焼室の表面積が広ければ一定時間におけ
る燃焼量が、増える為、一定時間における燃焼量に比例
して進力も増加する。このような考え方から図３の燃焼
室（３）に対して第５図、第６図の様な燃焼室に縦溝
（４）の付いた燃焼室が考えられ、使用されそれなりの
進力が発生されて来た。しかしながら、上記の燃焼室に
縦溝を付けて、燃料の燃焼面積を増加し進力を増強する
という考え方には限界が有った。本発明は、固体燃料ロ
ケットの燃焼室の形状が円柱形で有る事を考え合わせ、
燃焼室の形状を、第１図及び第２図の様に複数の横溝
（ドーナッツ形の溝）を増加形成する事により一定時間
内の燃焼量を増加する事が出来、これにより進力の増加
をはかる事が出来る発明である。すなわち、その目的は
円柱形の固体燃料燃焼室に燃焼面積増加用の複数の横溝
（ドーナッツ形の溝）を付ける事による進力の増加及
び、ロケットの性能の向上を図ることである。 The shape of the combustion chamber of the conventional solid fuel rocket is shown in FIGS. 3, 4, 5 and 6.
The solid fuel contains an oxidant, so if the surface area of the fuel combustion chamber is large, the amount of combustion in a certain period of time will increase. It also increases your initiative . From such a concept , the combustion shown in FIG.
A vertical groove is formed in the combustion chamber as shown in FIGS. 5 and 6 for the chamber (3) .
A combustion chamber with (4) was conceived and used, and a certain amount of advance was generated. However, there is a limit to the concept of providing a vertical groove in the above-mentioned combustion chamber to increase the combustion area of the fuel and increase the advance. The present invention considers that the shape of the combustion chamber of the solid fuel rocket is cylindrical,
The shape of the combustion chamber, it is possible to increase the combustion amount in a predetermined time by increasing forming a plurality of lateral grooves (grooves of the donut-shaped) as the FIGS. 1 and 2, an increase of the advance force by which It is an invention that can be measured. In other words, the purpose <br/> increase in multiple lateral grooves advancing force by putting the (groove of donut) for combustion area increases cylindrical solid fuel combustion chamber, and, by improving the performance of the rocket is there.
【０００４】[0004]
【課題を解決するための手段】本発明は固体燃料ロケッ
トの燃焼室にドーナッツ形の溝を複数設ける事により進
力の増加をはかる事が出来るもので、固体燃料ロケット
の燃焼室に燃焼面積増加用の複数のドーナッツ形の横溝
を設けたことを特徴とする。SUMMARY OF THE INVENTION According to the present invention, a solid fuel rocket is provided with a plurality of donut-shaped grooves in a combustion chamber of a solid fuel rocket so as to increase the power.
Donut-shaped lateral grooves in the combustion chamber for increased combustion area
Is provided .
【０００５】[0005]
【作用】従来の固体燃料ロケットの燃焼室（第５図、第
６図に示したもの）にドーナッツ形の横溝、第１図、第
２図における符号（５）を複数設けた事により固体燃料
ロケットの燃焼面積の増加が図られ大幅な進力増加が達
成される。[Action] combustion chamber of the conventional solid fuel rocket lateral grooves toroidal in (FIG. 5, was that shown in FIG. 6), the first view, a solid fuel by which a plurality of code (5) in FIG. 2 increase is achieved is significant Susumuryoku increase in the combustion area of the rocket reaches
Is done .
【０００６】[0006]
【実施例】従来形固体燃料ロケットの燃焼室の形状であ
る第３図、第４図、及び、第５図、第６図に示した燃焼
室（３）や縦溝（４）に加えて、本発明では第１図、第
２図の様にドーナッツ形の溝（５）を複数設け（例え
ば、図示した実施例では１４個設けられている）、燃料
の燃焼面積を増加し、一定時間内の燃焼量を増加するよ
うにしている。これにより進力の増加が達成される。ま
た、この横溝であるドーナッツ形の溝（５）をスパイラ
ル形状の溝にする事も出来、同様に燃料の燃焼面積の増
加が可能である。 EXAMPLES shape der combustion chamber of conventional type solid fuel rocket
Figure 3 that, FIG. 4, and FIG. 5, shown in Figure 6 combustion
In addition to the chamber (3) and the vertical groove (4), in the present invention, a plurality of donut-shaped grooves (5) are provided as shown in FIGS.
For example, in the illustrated embodiment, 14 fuel cells are provided.)
To increase the combustion area within a certain period of time.
I'm trying. This achieves an increase in drive. It is also possible to make grooves (5) of de Nattsu type is this lateral groove to groove in a spiral shape, as well as increasing the combustion area of the fuel
Addition is possible.
【０００７】[0007]
【発明の効果】本発明である横溝（ドーナッツ形の溝）
の付いた固体燃料燃焼室を使用する事により燃料の燃焼
面積を増加させる事ができ、これにより固体燃料ロケッ
トの大幅な進力増加及び性能の向上という効果が生じ
る。EFFECT OF THE INVENTION The lateral groove (donut-shaped groove ) of the present invention
Combustion area of the fuel can be Ru increase by using the marked with solid fuel combustion chamber, thereby resulting effect that substantial Susumuryoku increase and improvement in performance of the solid fuel rocket
You .
【図１】本発明の横溝付き（ドーナッツ形）固体燃料燃
焼室の縦断面図である。 FIG. 1 is a longitudinal sectional view of a solid fuel combustion chamber with a lateral groove (donut shape) according to the present invention .
【図２】本発明の横溝付き（ドーナッツ形）固体燃料燃
焼室の横断面図である。 FIG. 2 is a cross-sectional view of a laterally grooved (donut-shaped) solid fuel combustion chamber of the present invention .
【図３】従来型の固体燃料燃焼室の縦断面図である。 FIG. 3 is a longitudinal sectional view of a conventional solid fuel combustion chamber .
【図４】従来型の固体燃料燃焼室の横断面図である。 FIG. 4 is a cross-sectional view of a conventional solid fuel combustion chamber .
【図５】従来型の固体燃料燃焼室の縦溝付き固体燃料燃
焼室の縦断面図である。 FIG. 5 is a longitudinal sectional view of a solid fuel combustion chamber with a longitudinal groove of a conventional solid fuel combustion chamber .
【図６】従来型の固体燃料燃焼室の縦溝付き固体燃料燃
焼室の横断面図である。 FIG. 6 is a cross-sectional view of a solid fuel combustion chamber with a longitudinal groove of a conventional solid fuel combustion chamber .
（１） ロケットの固体燃料ケース （２） ロケットの固体燃料 （３） 固体燃料ロケットの従来型の燃焼室の形状 （４） 固体燃料ロケットの従来型縦溝付き燃焼室の形
状 （５） 固体燃料ロケットの本発明による横溝付き燃焼
室の形状(1) Rocket solid fuel case (2) Rocket solid fuel (3) Solid fuel rocket conventional combustion chamber shape (4) Solid fuel rocket conventional vertical grooved combustion chamber shape (5) Solid fuel Shape of combustion chamber with lateral grooves according to the present invention for rocket
Claims (2)
加用の複数のドーナッツ形の横溝を設けたことを特徴と
する固体燃料ロケット燃焼室の形状。1. The combustion area of a solid fuel rocket combustion chamber is increased.
It is characterized by providing multiple donut shaped lateral grooves for addition
Solid fuel rocket combustion chamber shape .
加用のスパイラル形の溝を設けたことを特徴とする固体
燃料ロケット燃焼室の形状。2. The combustion area of a solid fuel rocket combustion chamber is increased.
Solid with a spiral groove for addition
Fuel rocket combustion chamber shape .
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP7243528A JP2721138B2 (en) | 1995-08-18 | 1995-08-18 | Solid fuel rocket combustion chamber shape |
| PCT/JP1996/001178 WO1997007331A1 (en) | 1995-08-18 | 1996-04-30 | Shape of combustion chamber of solid fuel rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP7243528A JP2721138B2 (en) | 1995-08-18 | 1995-08-18 | Solid fuel rocket combustion chamber shape |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH0953510A JPH0953510A (en) | 1997-02-25 |
| JP2721138B2 true JP2721138B2 (en) | 1998-03-04 |
Family
ID=17105250
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP7243528A Expired - Lifetime JP2721138B2 (en) | 1995-08-18 | 1995-08-18 | Solid fuel rocket combustion chamber shape |
Country Status (2)
| Country | Link |
|---|---|
| JP (1) | JP2721138B2 (en) |
| WO (1) | WO1997007331A1 (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2145673C1 (en) * | 1999-05-25 | 2000-02-20 | Пермский завод им.С.М.Кирова | Solid propellant charge |
| RU2145674C1 (en) * | 1999-06-10 | 2000-02-20 | Пермский завод им.С.М.Кирова | Solid propellant charge |
| RU2178092C2 (en) * | 1999-11-01 | 2002-01-10 | Государственное унитарное предприятие "Научно-исследовательский институт полимерных материалов" | Solid-propellant charge for engine |
| JP6574255B2 (en) * | 2014-09-16 | 2019-09-11 | エアロジェット ロケットダイン インコーポレイテッド | Rocket motor with energy grains with microvoids |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4052943A (en) | 1976-09-16 | 1977-10-11 | The United States Of America As Represented By The Secretary Of The Navy | Coating composition and method for improving propellant tear strength |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3434426A (en) * | 1956-11-30 | 1969-03-25 | Jay W De Dapper | Combined ignitor and propellent grain |
-
1995
- 1995-08-18 JP JP7243528A patent/JP2721138B2/en not_active Expired - Lifetime
-
1996
- 1996-04-30 WO PCT/JP1996/001178 patent/WO1997007331A1/en not_active Ceased
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4052943A (en) | 1976-09-16 | 1977-10-11 | The United States Of America As Represented By The Secretary Of The Navy | Coating composition and method for improving propellant tear strength |
Also Published As
| Publication number | Publication date |
|---|---|
| JPH0953510A (en) | 1997-02-25 |
| WO1997007331A1 (en) | 1997-02-27 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| RVTR | Cancellation due to determination of trial for invalidation |