CN202596923U - Airborne solid rocket engine casing - Google Patents
Airborne solid rocket engine casing Download PDFInfo
- Publication number
- CN202596923U CN202596923U CN 201220164854 CN201220164854U CN202596923U CN 202596923 U CN202596923 U CN 202596923U CN 201220164854 CN201220164854 CN 201220164854 CN 201220164854 U CN201220164854 U CN 201220164854U CN 202596923 U CN202596923 U CN 202596923U
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- thickened
- thickness
- solid rocket
- thickening
- hanger
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- Expired - Fee Related
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Abstract
The utility model provides an airborne solid rocket engine casing, which includes a column section part, two lifting lug supports on the column section part, a front ellipsoid body, a front skirt, a front joint, a rear joint, a cable guard support and a strake wing support, wherein wall thickening rings are distributed on the column section part of the casing, and include lifting lug thickening rings at the two lifting lug mounting positions, two intermediate thickening rings between the two lifting lugs and a tail thickening ring adjacent to the tail part; the lifting lug thickening ring has the thickness Delta 1 equal to 4 to 4.5mm, the intermediate thickening ring has the thickness Delta 2 equal to 6 to 6.5mm, and the tail thickening ring has the thickness Delta 3 equal to 5.5 to 6.0mm; the intermediate thickening ring has the width H equal to 60 to 65mm, and the distance L between the two intermediate thickening rings is matched with a rack. According to the airborne solid rocket engine casing, a thin wall deformation buffering ring is arranged on the front side of the tail thickening ring, and the thickness Delta 4 of the thin wall deformation buffering ring is equal to the thickness of the casing wall.
Description
Technical field
The utility model belongs to Space Dynamic's technical field, is specifically related to a kind of airborne solid rocket motor case that is used for.
Background technique
Solid rocket motor case comprises front connector, preceding spheroid, preceding skirt, shell of column part, back joint and cable cover bearing, and wall thickness is the identical wall thickness that promptly waits except that the joint of front and back, and incompatibility hangs on the aircraft bottom and launches the Environmental Conditions of separating.The utility model has been filled up the blank of this aspect of solid rocket motor case.The utility model has adopted the cylinder of multiple wall thickness; Through on cylinder, adopting butt-welded mode to be provided for the required connection interface of aircraft hanger; The extension that has satisfied the major diameter solid propellant rocket flies and launches separation requirement; The strake wing bearing is used for the installation of strake wing, has solved major diameter, long-range launches intensity, the rigidity problem of solid rocket motor case under the Separating force condition at aircraft high overload, height, and provides corresponding interface to be used for the connection of all the other sections.
Summary of the invention
To be that design is a kind of be used for airborne solid rocket motor case to the purpose of the utility model, satisfies the aircraft on-hook and launch the needs of solid separated rocket motor.
The technological scheme of the utility model: the airborne solid rocket motor case that is used for of the utility model comprises the shell of column part, two hanger bearings on the shell of column part, preceding spheroid; Preceding skirt, front connector, back joint, cable cover bearing; The strake wing bearing is distributed with the wall thickness thickened on housing shell of column part, the wall thickness thickened comprises the hanger thickened of two hanger installation places; Two middle part thickened between two hangers are near the afterbody thickened of afterbody.
The thickness δ 1=4～4.5mm of described hanger thickened; The thickness δ 2=6～6.5mm of middle part thickened; The thickness δ 3=5.5～6.0mm of afterbody thickened.
Width H=60～the 65mm of described middle part thickened, two distance L and the hangers of middle part between the thickened are complementary.
Describedly be used for airborne solid rocket motor case, establish thin-walled distortion buffering ring in the front side of afterbody thickened; The thickness δ 4 of thin-walled distortion buffering ring equals housing wall thickness δ=2.8mm.
Intermediate location between the different wall adopts the arc transition of radius R=5～20mm.
The advantage of the utility model: the solid rocket motor case of the utility model is according to the function needs of motor; And alleviate the passive quality of solid propellant rocket as far as possible; There is the hanger thickened at the shell of column position at the position of welding hanger bearing, satisfies hanger bearing weld strength needs; Two middle part thickened between two hangers had both satisfied the working strength and the rigidity requirement of solid propellant rocket, had effectively alleviated the passive quality of motor simultaneously.The position is used to bear distortion and loss of weight between two middle part thickened;
Description of drawings
Fig. 1 is the motor body general structure schematic representation of the utility model.
Fig. 2 is the housing longitudinal cross-section schematic representation of Fig. 1.
Embodiment
Below in conjunction with accompanying drawing and instance the utility model is done explanation in further detail.
Like Fig. 1, shown in Figure 2, the airborne solid rocket motor case that is used for of the utility model comprises shell of column part 1, two hanger bearings 2 on the shell of column part 1; Preceding spheroid 3, preceding skirt 4, front connector 5; Back joint 6, cable cover bearing 7, strake wing bearing 8 is distributed with the wall thickness thickened on housing shell of column part 1; The wall thickness thickened comprises the hanger thickened 1a of two hanger installation places, and two middle part thickened 1b between two hangers are near the afterbody thickened 1c of afterbody.
Thickness δ 1=4～4.5mm of described hanger thickened 1a; Thickness δ 2=6～6.5mm of middle part thickened 1b; Thickness δ 3=5.5～6.0mm of afterbody thickened 1c.
Distance L and hanger between the width H=60～65mm of described each middle part thickened 1b, two middle part thickened 1b are complementary, and satisfied extension flies and launch separation requirement.Distance between described two middle part thickened is complementary with hanger.
Establish thin-walled distortion buffering ring 1d in the front side of afterbody thickened 1c; The thickness δ 4 of thin-walled distortion buffering ring 1d equals housing wall thickness δ=2.8mm (housing minimum wall thickness (MINI W.)).
The utility model is designed to the structure of the many wall thickness of shell of column with solid rocket motor case, through spinning process housing shell of column 1 is become wall thickness spinning, and the intermediate location between the different wall adopts the arc transition of radius R=5～20mm.
Housing shell of column 4 adopts many wall thickness design; Have 4 kinds of wall thickness; Wherein thickness δ position is the part that the housing minimum wall thickness (MINI W.) promptly satisfies casing rigidity, and thickness δ 1 is used for the welding of hanger bearing, and thickness δ 2 positions are used for the aircraft hanger and launch the contact of push rod and the installation of anti-pendulum stopper; Thickness δ 3, δ 4 positions are used to reduce the distortion at thin-walled position for the distortion buffering ring.
Above-mentioned instance is just in order to further specify the technological scheme of the utility model, and the protection domain of the utility model is not limited to this.
Claims (5)
1. one kind is used for airborne solid rocket motor case, comprises shell of column part (1), two the hanger bearings (2) on the shell of column part (1); Preceding spheroid (3), preceding skirt (4), front connector (5); Back joint (6), cable cover bearing (7), strake wing bearing (8); It is characterized in that: on housing shell of column part (1), be distributed with the wall thickness thickened; The wall thickness thickened comprises the hanger thickened (1a) of two hanger installation places, and two middle part thickened (1b) between two hangers are near the afterbody thickened (1c) of joint area behind the housing.
2. according to claim 1ly be used for airborne solid rocket motor case, it is characterized in that: the thickness δ 1=4～4.5mm of hanger thickened (1a); The thickness δ 2=6～6.5mm of middle part thickened (1b); The thickness δ 3=5.5～6.0mm of afterbody thickened (1c).
3. according to claim 1 and 2ly be used for airborne solid rocket motor case, it is characterized in that: the width H=60～65mm of middle part thickened (1b), distance L and hanger between two middle part thickened (1b) are complementary.
4. according to claim 1 and 2ly be used for airborne solid rocket motor case, it is characterized in that: establish thin-walled distortion buffering ring (1d) in the front side of afterbody thickened (1c); The thickness δ 4 of thin-walled distortion buffering ring (1d) equals the housing wall thickness.
5. according to claim 1 and 2ly be used for airborne solid rocket motor case, it is characterized in that: the intermediate location between the different wall adopts the arc transition of radius R=5～20mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220164854 CN202596923U (en) | 2012-04-18 | 2012-04-18 | Airborne solid rocket engine casing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220164854 CN202596923U (en) | 2012-04-18 | 2012-04-18 | Airborne solid rocket engine casing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202596923U true CN202596923U (en) | 2012-12-12 |
Family
ID=47314470
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220164854 Expired - Fee Related CN202596923U (en) | 2012-04-18 | 2012-04-18 | Airborne solid rocket engine casing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202596923U (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103244309A (en) * | 2013-04-28 | 2013-08-14 | 湖北航天技术研究院总体设计所 | Solid rocket punching composite engine shell |
| CN104696105A (en) * | 2013-12-10 | 2015-06-10 | 上海新力动力设备研究所 | Variable thickness housing of solid rocket engine |
| CN107052605A (en) * | 2016-12-18 | 2017-08-18 | 内蒙古航天红岗机械有限公司 | The assembling positioning tool and method of a kind of solid propellant rocket cable block |
| CN109736969A (en) * | 2018-12-11 | 2019-05-10 | 上海新力动力设备研究所 | A kind of solid propellant rocket spinning shell of part convex |
| CN110076259A (en) * | 2019-05-29 | 2019-08-02 | 湖北三江航天江北机械工程有限公司 | The processing method of airborne pencil rocket burning chamber shell |
| CN111515620A (en) * | 2020-04-10 | 2020-08-11 | 湖北三江航天江北机械工程有限公司 | Forming method of solid rocket engine shell |
-
2012
- 2012-04-18 CN CN 201220164854 patent/CN202596923U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103244309A (en) * | 2013-04-28 | 2013-08-14 | 湖北航天技术研究院总体设计所 | Solid rocket punching composite engine shell |
| CN103244309B (en) * | 2013-04-28 | 2016-01-20 | 湖北航天技术研究院总体设计所 | A kind of solid-rocket punching press combined engine housing |
| CN104696105A (en) * | 2013-12-10 | 2015-06-10 | 上海新力动力设备研究所 | Variable thickness housing of solid rocket engine |
| CN107052605A (en) * | 2016-12-18 | 2017-08-18 | 内蒙古航天红岗机械有限公司 | The assembling positioning tool and method of a kind of solid propellant rocket cable block |
| CN109736969A (en) * | 2018-12-11 | 2019-05-10 | 上海新力动力设备研究所 | A kind of solid propellant rocket spinning shell of part convex |
| CN110076259A (en) * | 2019-05-29 | 2019-08-02 | 湖北三江航天江北机械工程有限公司 | The processing method of airborne pencil rocket burning chamber shell |
| CN111515620A (en) * | 2020-04-10 | 2020-08-11 | 湖北三江航天江北机械工程有限公司 | Forming method of solid rocket engine shell |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20121212 Termination date: 20150418 |
|
| EXPY | Termination of patent right or utility model |