CN203847275U - Composite propellant engine - Google Patents
Composite propellant engine Download PDFInfo
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- CN203847275U CN203847275U CN201420081195.2U CN201420081195U CN203847275U CN 203847275 U CN203847275 U CN 203847275U CN 201420081195 U CN201420081195 U CN 201420081195U CN 203847275 U CN203847275 U CN 203847275U
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- front head
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- lining
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Abstract
Disclosed is a composite propellant engine. The composite propellant engine is characterized in that one end of a grain is placed and fixed into a connecting piece of a spray pipe, the other end face of the grain is adjacent to the inner end face of a front head, and expansion clearance of the grain is reserved between one end of the grain and the other end face of the grain; an initial-state combustion chamber is arranged in a shell, one end of the spray pipe in the initial state combustion chamber is located outside the other end face of the shell, and the other end of the spray pipe of the initial-state combustion chamber is located outside the other end face of the shell; one end of an igniter is located in the front head of the initial state combustion chamber and is connected with the front head; the other end of the igniter extends into the center hole of the grain; a plug cover is adhered to an expansion section of the spray pipe; a bushing is located in the shell and sleeves the outer surface of the initial state combustion chamber. By the arrangement, technical problems that the composite propellant engine is low in strength, poor in rigidity, prone to bending deformation under the action of winding pre-tightening force of glass filaments and incapable of directly winding composite shell outside the grain are solved, production cost is low, and batch production of the engine can be realized.
Description
Technical field
The present invention relates to solid propellant rocket field, specifically a kind of non-metal shell composite propellant motor.
Background technique
In rocket power plant, conventional composite propellant motor has following characteristics:
(1) as a part for body structure, for forming the pressurized firing chamber of engine operation, make the heat energy of propellant combustion product change into kinetic energy.Wherein motor body can adopt metal machining part or nonmetallic composite twisting member.
(2) composite propellant, because energy is high, is widely used on various solid propellant rockets at present, and the composite propellant powder charge design for different realizes by two kinds of charging means:
Be the free type of feed of powder column, powder column need be cast in jacket, during general assembly, more adiabatic powder column is freely seated in housing, and powder charge process and structural member working process can be carried out simultaneously, with short production cycle, and technique is relatively simple.For composite propellant, due to characteristics such as the intensity of powder column own are low, specific elongation is high, this charge structure is more common in cigarette burning Types of Medicine, can only provide low thrust long internal ballistics attributes, is mainly used in sustainer motor, is suitable for metal shell motor.This charge process, it is fewer that composite propellant is used, and uses comparatively generally on double base propellant.
The adherent cast form of another kind of employing, requires engine structure part to process in advance, and then order thermal insulation, powder charge, make motor charge become as a whole with case bonding.Due to the technological requirement of making, in being generally suitable for, the production of major diameter product, motor body can be metalwork, can be also Filament Wound Composite part.This technique integral production cycle is long, can meet the demand of different motor internal ballistics attributes by different three-dimensional medicine shape designs, uses more extensively, is common in booster, but is not suitable for small-bore motor charge.
Summary of the invention
For solving a technique difficult problem for the low and composite propellant band medicine wound composite housing of small-bore engine power, the present invention proposes a kind of composite propellant motor.
The present invention includes initial state firing chamber, housing, igniter and blanking cover.Described initial state firing chamber comprises front head, powder column, lining and jet pipe.One end of described powder column packs into and is fixed in this jet pipe linkage section, and another end face of powder column is adjacent with the interior edge face of front head, has the gap of 1～15mm between the two, the clearance for expansion that this gap is powder column.Described initial state firing chamber is positioned at housing, and the front end of the front head in initial state firing chamber is positioned at outside an end face of housing; One end of jet pipe in initial state firing chamber is positioned at outside another end face of housing.One end of igniter is arranged in the front head of initial state firing chamber, and is threaded with described front head; The other end of igniter extends in the center hole of powder column.Blanking cover is bonded in the diffuser of described jet pipe.Lining is positioned at housing, and is sleeved on the outer surface of initial state firing chamber.
The maximum outside diameter of described front head mates with the internal diameter of the lining coordinating, and both gaps are 0.2～0.5mm approximately; The minimum outer diameter section of front head is thread section, for docking with body structure part.The internal surface of front head is stepped, and internal whorl diameter, length match with the boundary dimension of the igniter of cooperation.There is circular groove at end face center in front head one end.After described front head coordinates with lining, powder column installation, the space of this groove has formed ignition space.
The wall thickness of described lining is 1.5～3mm, and lining internal diameter coordinates with the larger diameter end of front head and jet pipe.
In the present invention, powder column is free end near one end, front head place, can carry out adaptability distortion with variation of ambient temperature, Quan guarantee the structural integrity of powder column within the scope of serviceability temperature.Front head, powder column, lining, jet pipe form an integral body, have formed the firing chamber of original state.Lining plays thermal insulation, sealing and supporting effect in whole motor, prevents that burning from appearring in motor in the course of the work, gas leak phenomenon.And by lining, improved the manufacturability that is wound around housing: utilize front head external surface and jet pipe diffuser that initial state firing chamber is fixed on Stetch Wrapping Machine, using this core as Stetch Wrapping Machine, adopt conventional method, the three-dimensional of carrying out motor body with high strength composite fiber is back and forth wound around, in layer until reach predetermined thickness, then winding body is solidified 2～4 days under the heat-retaining condition of 50～60 ℃, guarantee to solidify completely, finally boundary dimension is carried out to the engine chamber that machining property becomes end-state.
The present invention has solved by the method at the exterior lining of powder column that composite propellant powder column intensity is low, poor rigidity, under the effect of glass yarn winding pretightening force, easily occur bending and deformation, cannot be outside powder column a direct technique difficult problem for wound composite housing, this technological method makes motor possess good sealed, thermally insulated effect simultaneously, has improved casing rigidity; Adopt the motor inner trajectory adaptability of this technique extensive, by adjusting Types of Medicine, can meet the internal ballistics attributes requirement of the motor of not planting purposes; Owing to adopting the high composite material casing of specific strength, reduced motor gross mass, mass ratio can be increased to more than 0.63.This forming method is because amount of parts is few, and the prices of raw and semifnished materials are low, has therefore simplified production technology, has reduced artificial and the cost of raw material, is suitable for batch production; Owing to having adopted high-octane composite propellant on the technique basis freely loading, motor can be realized the mentality of designing of high thrust, high quality ratio, therefore can be the flight dynamic devices that the multiple rocket products such as rainfall-increasing and anti-hail rocket, space probe provide high-quality, to carry the useful load of larger quality or higher range is provided, complete or realize specific job task.
The present invention compared with prior art tool has the following advantages:
1 this forming method makes motor inner trajectory adaptability extensive, can utilize composite propellant to realize free filling process, meets the totally inner trajectory demand to motor of bullet, simultaneously owing to having used bush structure, makes adiabatic reliable, the good seal of motor.
2 because composite propellant powder column can carry out adaptability distortion with variation of ambient temperature in initial state firing chamber, Quan therefore can guarantee the Structural Integrity of Propellant Grains of motor within the scope of serviceability temperature;
3 breakthrough realizations the band medicine winding shaping process of composite propellant powder column motor body, by practical operation, verify that this technological method is simply ripe, cost is low, can realize the batch production of motor.
Accompanying drawing explanation
Accompanying drawing 1 is front head structural representation;
Accompanying drawing 2 is nozzle structure schematic diagram;
Accompanying drawing 3 is Grain structure plan views;
Accompanying drawing 4 is Grain structure side views;
Accompanying drawing 5 is bush structure schematic diagram;
Accompanying drawing 6 is initial state chamber structure schematic diagram;
Accompanying drawing 7 is structural representations of the present invention.
In figure: 1. front head; 2. powder column; 3. lining; 4. jet pipe; 5. housing; 6. igniter; 7. blanking cover.
Embodiment
The present embodiment is a kind of composite propellant motor, comprises initial state firing chamber, housing 5, igniter 6 and blanking cover 7.Described initial state firing chamber is positioned at housing 5, and the front end of the front head 1 in initial state firing chamber is positioned at outside an end face of housing 5; One end of jet pipe 4 in initial state firing chamber is positioned at outside another end face of housing 5.One end of igniter 6 is arranged in the front head 1 of initial state firing chamber, and is threaded with described front head 1; The other end of igniter 6 extends in the center hole of powder column 2.Blanking cover 7 is bonded in the diffuser of described jet pipe 4.
Described initial state firing chamber comprises front head 1, powder column 2, lining 3 and jet pipe 4.
The external peripheral surface of described powder column 2 is stepped, and the external diameter of the smaller diameter end of one end is identical with the internal diameter of jet pipe 4 linkage sections, and the smaller diameter end of powder column 2 is packed in jet pipe 4 linkage sections, is threaded connection.Another end face of powder column 2 is adjacent with the interior edge face of front head 1, has the gap of 1～15mm between the two, the clearance for expansion that this gap is powder column.In the present embodiment, described clearance for expansion is 5mm.Lining 3 is positioned at housing 1, and is sleeved on the outer surface of initial state firing chamber
Front head 1 is hollow solid of rotation.The external peripheral surface of described front head 1 is stepped, and the maximum outside diameter of this excircle mates with the internal diameter of the lining coordinating 3, and both gaps are 0.2～0.5mm approximately; The minimum outer diameter section of front head 1 is thread section, for docking with body structure part.The internal surface of front head 1 is stepped, and internal whorl diameter, length match with the boundary dimension of the igniter 6 of cooperation.There is circular groove at end face center in front head 1 one end.After described front head 1 is installed and coordinated with lining 3, powder column 2, the space of this groove has formed ignition space.
Powder column 2 is hollow article.The external diameter of described powder column 2 is less than the internal diameter 1mm left and right of lining 3, and one end of this powder column 2 is stepped, has formed smaller diameter end, and the screw thread in smaller diameter end is for being connected with the internal thread of jet pipe 4, and the length of smaller diameter end is slightly less than the length in jet pipe 4 isometrical holes.The aperture of powder column 2 endoporus is greater than the external diameter 6～20mm of igniter 6.Powder column inside is hollow form, and the shape of interior profile, size can be carried out accommodation according to motor index request.
Lining 3 is also thin wall shape solid of rotation, adopts high strength nonmetallic material fiber to roll and form from level to level.The wall thickness of lining 3 is 1.5～3mm approximately, and lining 3 internal diameters coordinate with the larger diameter end of front head 1 and jet pipe 4.
Jet pipe 4 is hollow solid of rotation.The external peripheral surface of jet pipe 4 is stepped, and its large end external diameter mates with the internal diameter of lining 3, and both gaps are 0.2～0.5mm approximately, and small end external diameter is for being connected with full projectile tail wing endoporus coupling.The endoporus of the large end of jet pipe 4 external diameter one end is tapped hole, for being threaded of powder column 2.Blast tube in jet pipe adopts Laval nozzle form, converging portion, throat, diffuser, consists of, and each constituent element requires coaxial with outer mold surface, and palpus smooth transition, has formed combustion gas contraction, the inflation channel of motor, and has produced thus motor power.
While forming initial state firing chamber, front head 1, powder column 2, lining 3,4 four parts of jet pipe are fitted together according to the state group of Fig. 7.Utilize powder column 2 with the screw thread on jet pipe 4, both to be connected, then lining 3 in powder column 2 outer cover, by the enlarged diameter section laminating of the internal diameter of lining 3 one end and jet pipe 4, the great circle cylinder laminating of the other end and front head 1, in joint place, stick with glue and connect, during assembling, should guarantee to have gap between one end of powder column 2 and front head 1, gap is 1～15mm approximately, and glue forms initial state firing chamber after solidifying completely.During making, should guarantee each element coaxial, connect fastening.Initial state firing chamber makes front head 1, powder column 2, lining 3, jet pipe 4 form an integral body, facilitates the carrying out of later stage manufacturing process.
Housing 5 is thin wall shape solid of rotation, adopts intensity to be greater than 2000MPa high-strength glass fibre, by twining of routine method processed, is made.The internal diameter of housing 5 is identical with the external diameter of initial state firing chamber.
Igniter 6 is existing mature technologies, the in-built ignition powder for the propellant agent that ignites.Its screw thread must mate with the internal thread of front connector 1.
Engine assembly.Utilize screw thread that igniter 6 rotations are fixed on the front head 1 of engine chamber, screw-down torque 15Nm, blanking cover 7 sticks with glue and is connected on jet pipe 4 diffusers and solidifies, and requires to guarantee to seal between igniter and firing chamber, firing chamber and blanking cover, forms thus motor.
Claims (3)
1. a composite propellant motor, is characterized in that, comprises initial state firing chamber, housing, igniter and blanking cover; Described initial state firing chamber comprises front head, powder column, lining and jet pipe; One end of described powder column packs into and is fixed in this jet pipe linkage section, and another end face of powder column is adjacent with the interior edge face of front head, has the gap of 1～15mm between the two, the clearance for expansion that this gap is powder column; Described initial state firing chamber is positioned at housing, and the front end of the front head in initial state firing chamber is positioned at outside an end face of housing; One end of jet pipe in initial state firing chamber is positioned at outside another end face of housing; One end of igniter is arranged in the front head of initial state firing chamber, and is threaded with described front head; The other end of igniter extends in the center hole of powder column; Blanking cover is bonded in the diffuser of described jet pipe; Lining is positioned at housing, and is sleeved on the outer surface of initial state firing chamber.
2. a kind of composite propellant motor as claimed in claim 1, is characterized in that, the internal diameter coupling of the maximum outside diameter of front head and the lining coordinating, and both gaps are 0.2～0.5mm approximately; The minimum outer diameter section of front head is thread section, for docking with body structure part; The internal surface of front head is stepped, and internal whorl diameter, length match with the boundary dimension of the igniter of cooperation; There is circular groove at end face center in front head one end; After described front head coordinates with lining, powder column installation, the space of this groove has formed ignition space.
3. a kind of composite propellant motor as claimed in claim 1, is characterized in that, the wall thickness of lining is 1.5～3mm, and lining internal diameter coordinates with the larger diameter end of front head and jet pipe.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420081195.2U CN203847275U (en) | 2014-02-25 | 2014-02-25 | Composite propellant engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420081195.2U CN203847275U (en) | 2014-02-25 | 2014-02-25 | Composite propellant engine |
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| CN201420081195.2U Expired - Fee Related CN203847275U (en) | 2014-02-25 | 2014-02-25 | Composite propellant engine |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105965866A (en) * | 2016-05-31 | 2016-09-28 | 湖北三江航天江北机械工程有限公司 | Integral forming method for engine case and spraying pipe |
| CN106217921A (en) * | 2016-07-25 | 2016-12-14 | 湖北三江航天江北机械工程有限公司 | Electromotor composite material casing integral formation method with jet pipe |
| CN106273599A (en) * | 2016-07-25 | 2017-01-04 | 湖北三江航天江北机械工程有限公司 | Electromotor composite material casing and jet pipe integral formation method |
| CN106870206A (en) * | 2017-03-29 | 2017-06-20 | 北京航空航天大学 | A kind of quick response solid-liquid rocket combines powder column |
| CN106930865A (en) * | 2017-02-24 | 2017-07-07 | 湖北航天技术研究院总体设计所 | The high-energy solid rocket engine that a kind of temperature wide is used |
| CN107100761A (en) * | 2017-06-29 | 2017-08-29 | 湖北三江航天江河化工科技有限公司 | A kind of test engine |
| CN107270312A (en) * | 2017-05-26 | 2017-10-20 | 北京航天发射技术研究所 | A kind of Metal Substrate ignition power device |
| CN109653900A (en) * | 2018-11-29 | 2019-04-19 | 湖北航天技术研究院总体设计所 | A kind of forming method of dipulse solid engines powder charge combustion chamber |
| CN109724832A (en) * | 2019-02-01 | 2019-05-07 | 西北工业大学 | A kind of collection device and collection method of solid propellant condensed-phase combustion product |
| CN110821708A (en) * | 2019-08-30 | 2020-02-21 | 南京理工大学 | Three-combustion-speed variable-thickness combined explosive column structure of jet pipe-free engine |
| CN111810318A (en) * | 2020-06-28 | 2020-10-23 | 北京凌空天行科技有限责任公司 | Single-chamber double-thrust solid rocket engine and rocket |
| CN111828196A (en) * | 2020-07-04 | 2020-10-27 | 张帅 | Aircraft engine tail nozzle |
| CN112571822A (en) * | 2020-10-29 | 2021-03-30 | 上海新力动力设备研究所 | Memory non-metal core mold structure suitable for winding with medicine and shell forming method |
| CN113958424A (en) * | 2021-08-20 | 2022-01-21 | 西安零壹空间科技有限公司 | Rocket boosting engine with inner trajectory curve free of tail warping phenomenon |
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2014
- 2014-02-25 CN CN201420081195.2U patent/CN203847275U/en not_active Expired - Fee Related
Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105965866B (en) * | 2016-05-31 | 2017-12-26 | 湖北三江航天江北机械工程有限公司 | Motor body and jet pipe integral formation method |
| CN105965866A (en) * | 2016-05-31 | 2016-09-28 | 湖北三江航天江北机械工程有限公司 | Integral forming method for engine case and spraying pipe |
| CN106217921A (en) * | 2016-07-25 | 2016-12-14 | 湖北三江航天江北机械工程有限公司 | Electromotor composite material casing integral formation method with jet pipe |
| CN106273599A (en) * | 2016-07-25 | 2017-01-04 | 湖北三江航天江北机械工程有限公司 | Electromotor composite material casing and jet pipe integral formation method |
| CN106930865A (en) * | 2017-02-24 | 2017-07-07 | 湖北航天技术研究院总体设计所 | The high-energy solid rocket engine that a kind of temperature wide is used |
| CN106870206A (en) * | 2017-03-29 | 2017-06-20 | 北京航空航天大学 | A kind of quick response solid-liquid rocket combines powder column |
| CN107270312A (en) * | 2017-05-26 | 2017-10-20 | 北京航天发射技术研究所 | A kind of Metal Substrate ignition power device |
| CN107100761B (en) * | 2017-06-29 | 2019-07-02 | 湖北三江航天江河化工科技有限公司 | A kind of test engine |
| CN107100761A (en) * | 2017-06-29 | 2017-08-29 | 湖北三江航天江河化工科技有限公司 | A kind of test engine |
| CN109653900A (en) * | 2018-11-29 | 2019-04-19 | 湖北航天技术研究院总体设计所 | A kind of forming method of dipulse solid engines powder charge combustion chamber |
| CN109653900B (en) * | 2018-11-29 | 2020-02-11 | 湖北航天技术研究院总体设计所 | Forming method of double-pulse solid engine charge combustion chamber |
| CN109724832A (en) * | 2019-02-01 | 2019-05-07 | 西北工业大学 | A kind of collection device and collection method of solid propellant condensed-phase combustion product |
| CN109724832B (en) * | 2019-02-01 | 2020-09-29 | 西北工业大学 | Device and method for collecting condensed-phase combustion products of solid propellant |
| CN110821708A (en) * | 2019-08-30 | 2020-02-21 | 南京理工大学 | Three-combustion-speed variable-thickness combined explosive column structure of jet pipe-free engine |
| CN111810318A (en) * | 2020-06-28 | 2020-10-23 | 北京凌空天行科技有限责任公司 | Single-chamber double-thrust solid rocket engine and rocket |
| CN111828196A (en) * | 2020-07-04 | 2020-10-27 | 张帅 | Aircraft engine tail nozzle |
| CN111828196B (en) * | 2020-07-04 | 2022-11-01 | 峰特(浙江)新材料有限公司 | Aircraft engine exhaust nozzle |
| CN112571822A (en) * | 2020-10-29 | 2021-03-30 | 上海新力动力设备研究所 | Memory non-metal core mold structure suitable for winding with medicine and shell forming method |
| CN113958424A (en) * | 2021-08-20 | 2022-01-21 | 西安零壹空间科技有限公司 | Rocket boosting engine with inner trajectory curve free of tail warping phenomenon |
| CN113958424B (en) * | 2021-08-20 | 2022-12-06 | 西安零壹空间科技有限公司 | Rocket boosting engine with inner trajectory curve free of tail warping phenomenon |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140924 Termination date: 20200225 |