CN112520060A - Unmanned aerial vehicle rocket booster - Google Patents
Unmanned aerial vehicle rocket booster Download PDFInfo
- Publication number
- CN112520060A CN112520060A CN202110000293.3A CN202110000293A CN112520060A CN 112520060 A CN112520060 A CN 112520060A CN 202110000293 A CN202110000293 A CN 202110000293A CN 112520060 A CN112520060 A CN 112520060A
- Authority
- CN
- China
- Prior art keywords
- combustion chamber
- top cover
- nozzle
- front top
- boss
- 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.)
- Pending
Links
- 238000002485 combustion reaction Methods 0.000 claims abstract description 84
- 238000007789 sealing Methods 0.000 claims abstract description 8
- 238000009413 insulation Methods 0.000 claims description 40
- 239000007921 spray Substances 0.000 claims description 33
- 210000001503 joint Anatomy 0.000 claims description 10
- 238000007796 conventional method Methods 0.000 claims description 6
- 230000000694 effects Effects 0.000 claims description 5
- 239000002360 explosive Substances 0.000 claims description 4
- 239000002737 fuel gas Substances 0.000 claims description 3
- 239000000843 powder Substances 0.000 claims description 3
- 230000007704 transition Effects 0.000 claims description 3
- 230000013011 mating Effects 0.000 claims 1
- 238000012360 testing method Methods 0.000 description 9
- 238000003754 machining Methods 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 4
- 238000013461 design Methods 0.000 description 3
- 239000007787 solid Substances 0.000 description 3
- 238000011161 development Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000011900 installation process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Launching or towing gear
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/15—Propulsion using combustion exhausts other than turbojets or turbofans, e.g. using rockets, ramjets, scramjets or pulse-reactors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
Abstract
An unmanned rocket booster is characterized in that a front top cover of an ellipsoid is positioned at the front end of a combustion chamber; the central positioning sleeve of the thrust rod is sleeved on the positioning boss at the center of the front top cover, and the end surface of the front end cover is attached to the end surface of the flange plate of the thrust rod. The convergent section of the nozzle is arranged at the rear end of the combustion chamber; a plug is mounted within the nozzle and is located within the diverging section of the nozzle. The head of the top cover is an ellipsoid, and under the same working internal pressure and the same safety factor, the ellipsoid is better in stress condition, the shell is lower in wall thickness, and the quality of the top cover can be effectively reduced. The invention improves the sealing performance of the connecting part and improves the assembly precision of the connecting part through the guide section; through the improvement to booster top cap and booster distance rod, realized the reduction of top cap with the distance rod assembly degree of difficulty, improved the thrust rod and the combustion chamber top cap and connected the atress condition, reduced the thrust deflection numerical value of booster.
Description
Technical Field
The invention relates to the technical field of solid rocket engines, in particular to an unmanned aerial vehicle rocket booster.
Background
In recent years, the market of unmanned aerial vehicles is very wide, the types and related design technologies of unmanned aerial vehicles are different day by day, and the development of corresponding accessory parts is also a sudden leap. The booster is used as an initial power source of the unmanned aerial vehicle, and the booster has no impact on the important position. With the continuous development of the unmanned aerial vehicle design technology, new requirements are provided for various performance indexes of the booster generally.
The most important indexes of the solid rocket engine as a booster are thrust deflection, average thrust and working time respectively. One of the important factors affecting the thrust deflection is the selection and design of the connection mode. Generally, unmanned aerial vehicle rocket booster is connected with unmanned aerial vehicle through the thrust rod. The existing connection mode of the booster of the unmanned aerial vehicle and the thrust rod mostly adopts a threaded connection mode, namely, the top cover of the booster is connected with the thrust rod in a threaded fit mode. In the machining and manufacturing processes of the thrust rod and the top cover, in order to ensure the precision of threaded connection, the structure and the machining process of the connecting position are complex, and the management and control requirements of the machining process are high.
When the booster is assembled, the operation level of an operator is required to be higher due to the limitation of threaded connection, otherwise, the phenomena of seizure of connecting threads, incomplete screwing of threads and the like can occur, so that the thrust deflection of the booster is larger, and the boosting launching effect is influenced.
Through search, in the invention creation with patent number CN201910174281.5, a rocket boosting device of unmanned aerial vehicle is disclosed. The invention provides a structural form for connecting a rocket booster and an unmanned aerial vehicle, and the connection mode of the bearing cylinder and the top cover is threaded connection. However, the threaded connection with higher precision is difficult to realize, the assembly process is complicated, and the connection between the booster and the thrust rod after assembly has unstable thrust deflection and is easily influenced by manual operation.
Disclosure of Invention
In order to overcome the defects of low assembly efficiency and unstable thrust deflection of the booster in the prior art, the invention provides an unmanned aerial vehicle rocket booster.
The invention comprises a thrust rod, a front top cover, a combustion chamber, a spray pipe, an igniter and a plug. Wherein the front top cover is positioned at the front end of the combustion chamber; and the central positioning sleeve of the thrust rod is sleeved on the positioning boss at the center of the front top cover, and the end surface of the front end cover is attached to the end surface of the flange plate of the thrust rod. The igniter is positioned in a cavity formed between the inner end surface of the front top cover and the front end surface of the combustion chamber, and one end of the igniter is positioned in the threaded blind hole of the inner end surface of the positioning lug boss of the front top cover. The nozzle and the plug are both in the prior art and assembled according to a conventional method, and the convergent section of the nozzle is installed at the rear end of the combustion chamber through threads; a plug is mounted within the nozzle and is located within the diverging section of the nozzle.
The thrust rod consists of a central positioning sleeve and a flange plate which are perpendicular to each other. The inner diameter of the central positioning sleeve is the same as the outer diameter of the positioning boss of the front top cover, and the central positioning sleeve and the positioning boss are in interference fit. The flange plate is evenly provided with connecting holes fixedly connected with the front top cover.
The front top cover is an ellipsoid; the thickness of the ellipsoid is 3 mm. The outer edge of the outer end face of the front top cover is provided with an annular connecting boss protruding axially, and a plurality of threaded holes are uniformly distributed in the boss. A front top cover positioning boss 10 axially protrudes from the center of the outer end surface of the front top cover, and a threaded blind hole for mounting an igniter is formed in the center of the inner end surface of the front top cover positioning boss; the length of the front top cover positioning boss is 15 mm. The annular connecting boss of the front top cover is a stress surface of the front top cover; the outer diameter of the annular connecting boss is 150mm, and the inner diameter of the annular connecting boss is 108 mm.
The outer surface of the shell close to one end of the front top cover is a matching surface with the shell of the combustion chamber; the outer surface of the shell is provided with three steps; in the three-stage steps, the step close to one end of the thrust rod forms a guide section of the combustion chamber shell, and when the threaded connection is carried out, the threaded connection butt joint precision is improved through the guide section, and the thrust deflection numerical value of the connection of the top cover and the combustion chamber is reduced; the length of the guide section is 10 mm. The middle part of the three-stage step is a thread surface connected with the combustion chamber; the step close to the end surface of the near end is a positioning surface matched with the combustion chamber shell to form a positioning spigot. And the surface of the third step is coated with putty of 0.2mm by a conventional method so as to enhance the sealing and heat-insulating effect of the third step.
The combustion chamber comprises a combustion chamber shell, a grain, a lining and a heat insulation layer. The heat insulation layer is adhered to the inner surface of the combustion chamber shell, and a secondary adhered heat insulation layer is arranged on the surface of the heat insulation layer at the matching section of the combustion chamber shell and the front top cover; the surface of the heat insulation layer of the combustion chamber shell and the matching section of the spray pipe is provided with a heat insulation layer which is adhered for the second time; the secondary adhesion heat insulation layer increases the sealing performance of the combustion chamber shell. And a lining layer is sprayed on the surface of the heat insulating layer. The explosive columns are filled in the combustion chamber shell through a charging mould in an adherence pouring mode and are solidified.
The lance includes a lance insulation, a lance housing, and a throat insert. The spray pipe heat insulation piece is adhered to the inner surface of the spray pipe shell; the throat insert is positioned at the throat of the nozzle insulation and is adhered to the inner surface of the nozzle insulation. The outer diameter of the front end of the spray pipe heat-insulating part is the same as the inner diameter of a boss on the inner circumferential surface of the combustion chamber, so that the spray pipe heat-insulating part and the combustion chamber are sealed through a step, and the end face of the front end of the spray pipe heat-insulating part is attached to the end face of a powder column in the combustion chamber. The throat insert is positioned at the throat of the nozzle insulation and is adhered to the inner surface of the nozzle insulation.
The heat-insulating part at the front part of the throat insert adopts large arc transition to ensure the flow stability of the fuel gas. A guide section is reserved at the front end of the thread of the spray pipe shell, and when the thread connection is carried out, the thread connection butt joint precision is improved through the guide section, and the thrust deflection numerical value of the connection of the top cover and the combustion chamber is reduced. The length of the guide section is 10 mm.
The head of the top cover is an ellipsoid, and under the same working internal pressure and the same safety factor, the ellipsoid is better in stress condition, the shell is lower in wall thickness, and the quality of the top cover can be effectively reduced. The top cover and the combustion chamber are connected in a threaded manner, and three sealing surfaces are reserved in the connecting structure, so that the connecting position is effectively sealed. A longer guide section is reserved at the connecting part, so that the circle jump detection value of the engine can be reduced when the threaded connection is carried out, and the thrust deflection numerical value of the connection of the top cover and the combustion chamber is reduced; the head of the top cover is provided with a positioning boss structure which plays a role in positioning and limiting when being assembled with the thrust rod.
The combustion chamber of the invention adopts a front and back large opening structure, the charging adopts wall-attached casting molding, and the mature three-component solid composite propellant is connected with the combustion chamber top cover and the spray pipe through screw threads. The front end and the rear end of the combustion chamber shell are provided with longer guide sections in front of threads so as to improve the butt joint precision of threaded connection.
The spray pipe adopts a conical fixed spray pipe and is in an integrated heat insulation form, consists of a spray pipe shell, a spray pipe heat insulation part and a throat liner and is connected with the combustion chamber through threads. The longer guide section is arranged after the spray pipe shell is in threaded connection, so that the threaded connection butt joint precision can be improved.
According to the invention, the structure of the top cover of the booster and the structure of the thrust rod of the booster are improved, so that the assembly difficulty of the top cover and the thrust rod is reduced, the stress condition of the connection between the thrust rod and the top cover of the combustion chamber is improved, and the thrust deflection numerical value of the booster is reduced.
In order to verify the effect of the invention, the main performance parameters of the booster are measured and evaluated through batch whole machine round jump numerical test and six-component force test, and the result shows that the invention reduces the difficulty of the final assembly of the booster, improves the production efficiency and the installation precision, and reduces the thrust deflection numerical value of the booster. After 30 times of ground static tests, flight test verification and six-component force test tests, the beneficial effects are specifically shown as follows:
1. the head of the front top cover adopts an ellipsoid, the wall thickness of the improved front top cover is 8mm, after the invention is adopted, the wall thickness of the front top cover is 3mm, and under the same safety coefficient, the wall thickness of the top cover is thinner and the quality is smaller.
2. The connection and positioning mode of the front top cover and the thrust rod is changed from threaded positioning into matching positioning of a boss at the top of the top cover and a central positioning sleeve, the round trip test value of the threaded connection booster is 0.30, the thrust deflection value is 0.8 degrees, and after the invention is adopted, the round trip test value of the booster is 0.18, and the thrust deflection value is 0.55 degrees. The connection positioning precision of the invention is higher, the circle jump test value of the booster can be effectively reduced, and the thrust deflection value is reduced.
3. Before improvement, the stress area of the contact between the top cover of the combustion chamber and the thrust rod is 0.08 square meter, and after the invention is adopted, the stress area of the contact between the top cover of the combustion chamber and the thrust rod is 0.8 square meter, so that the stress area is increased, and the stress condition is better.
4. Before improvement, 3 workers are needed in the installation process of the booster thrust rod and the booster, the consumed working hours are 0.4 hour, after improvement, 2 workers are needed in the installation process of the booster thrust rod and the booster, the consumed working hours are 0.3 hour, the labor cost is reduced, and the manufacturing cost of the engine top cover and the thrust rod is also reduced by about 5%. The invention realizes the reduction of the assembly difficulty and the manufacturing cost of the thrust rod and the booster.
Drawings
Fig. 1 is a schematic view of the structure of the booster of the present invention.
FIG. 2 is a schematic view of the mounting of the improved front cover of the booster with the thrust rod and the igniter.
FIG. 3 is a schematic view of the booster top cover, thrust rod and igniter assembly of the present invention.
FIG. 4 is a schematic view of a thrust rod configuration; wherein fig. 4a is a front view and fig. 4b is a left side view of fig. 4 a.
FIG. 5 is a schematic view of a front header construction; wherein fig. 5a is a front view and fig. 5b is a left side view of fig. 5 a.
Fig. 6 is a schematic view of the combustion chamber structure.
FIG. 7 is a schematic view of the nozzle configuration.
FIG. 8 is a schematic view of a nozzle plugging configuration.
Fig. 9 is a schematic view of the igniter configuration.
In the figure: 1. a thrust rod; 2. a top cover; 3. a combustion chamber; 4. a nozzle; 5. a screw; 6. an igniter; 7. blocking; 8. a central positioning sleeve; 9. connecting holes; 10. positioning the boss; 11. a top cover threaded hole; 12. a combustion chamber housing; 13. carrying out grain treatment; 14. a liner and a thermal insulation layer; 15. a nozzle insulation; 16. a nozzle housing; 17. a throat insert.
Detailed Description
The embodiment is a rocket booster for a certain type of unmanned aerial vehicle, and the rocket booster comprises a thrust rod 1, a front top cover 2, a combustion chamber 3, a spray pipe 4, a screw 5, an igniter 6 and a plug 7. Wherein the front top cover 2 is positioned at the front end of the combustion chamber 3; and a central positioning sleeve 8 of the thrust rod is sleeved on a positioning boss at the center of the front top cover, and the end surface of the front end cover is attached to the end surface of the flange plate of the thrust rod. The igniter 6 is positioned in a cavity formed between the inner end surface of the front top cover and the front end surface of the combustion chamber, and one end of the igniter is positioned in the threaded blind hole of the inner end surface of the positioning lug boss of the front top cover; the igniter 6 is of the prior art. The nozzle 4 and the plug 7 are both in the prior art and are assembled according to a conventional method, and the convergent section of the nozzle is installed at the rear end of the combustion chamber through threads; a plug 7 is mounted within the lance and is located within the expanded section of the lance.
The thrust rod 1 is in a transverse T shape and consists of a central positioning sleeve 8 and a flange plate which are vertical to each other. The inner diameter of the central positioning sleeve is the same as the outer diameter of the positioning boss of the front top cover, and the central positioning sleeve and the positioning boss are in interference fit. The flange plate is evenly provided with connecting holes 9 fixedly connected with the front top cover 2.
In the embodiment, the inner diameter of the central positioning sleeve 8 is phi 30mm, and the central positioning sleeve is matched with the front top cover positioning boss 10 to play a positioning role; and 4 groups of eight connecting holes 9 with the diameter of 8.5mm are designed on the thrust rod flange, and the positions of the connecting holes correspond to the positions of the top cover threaded holes.
The front top cover 2 is a hollow revolving body. The surface of the front top cover is an ellipsoid; the thickness of the ellipsoid is 3mm, which is smaller than that of the flat plate structure, and the structure weight of the top cover is reduced under the condition of meeting the same internal pressure and the same safety factor. The outer edge of the outer end face of the front top cover is provided with an annular connecting boss protruding axially, and a plurality of threaded holes are uniformly distributed in the boss. A front top cover positioning boss 10 axially protrudes from the center of the outer end surface of the front top cover, and a threaded blind hole for mounting an igniter 6 is formed in the center of the inner end surface of the front top cover positioning boss; the length of the front top cover positioning boss is 15 mm. The annular connecting boss of the front top cover is a stress surface of the front top cover; the outer diameter of the annular connecting boss is 150mm, and the inner diameter of the annular connecting boss is 108 mm.
The outer surface of the shell close to one end of the front top cover is a matching surface with the shell of the combustion chamber; the outer surface of the shell is provided with three steps; in the three-stage steps, the step close to one end of the thrust rod 1 forms a guide section of the combustion chamber shell, and when the threaded connection is carried out, the threaded connection butt joint precision is improved through the guide section, and the thrust deflection numerical value of the connection of the top cover and the combustion chamber is reduced; the length of the guide section is 10 mm. The middle part of the three-stage step is a thread surface connected with the combustion chamber; the step close to the end surface of the near end is a positioning surface matched with the combustion chamber shell to form a positioning spigot. And the surface of the third step is coated with putty of 0.2mm by a conventional method so as to enhance the sealing and heat-insulating effect of the third step.
The combustion chamber 3 comprises a combustion chamber housing 12, a charge 13, a liner and a thermal insulation layer 14. The combustion chamber shell is a thin-wall cylinder, and two ends of the combustion chamber shell are respectively connected with the front top cover and the spray pipe through threads. The heat insulation layer is adhered to the inner surface of the combustion chamber shell, and the heat insulation layer is secondarily adhered to the surface of the heat insulation layer at the matching section of the combustion chamber shell and the front top cover; the surface of the heat-insulating layer of the combustion chamber shell and the matching section of the spray pipe is secondarily adhered with the heat-insulating layer; and the heat insulation layer is secondarily adhered to the front top cover matching section and the spray pipe matching section so as to strengthen the sealing of the combustion chamber shell. A lining layer is sprayed on the surface of the heat insulating layer 14. The explosive column 13 is filled and solidified in the combustion chamber shell 12 through an explosive charging mould in an adherence pouring mode.
The nozzle 4 is of the prior art. The lance is an insulated integrated structure comprising a lance insulation 15, a lance housing 16 and a throat insert 17. The spray pipe heat insulation piece is adhered to the inner surface of the spray pipe shell; the throat insert 17 is glued to the nozzle insulation. The convergent section of the lance is connected to the combustion chamber by means of a screw thread. The outer diameter of the front end of the spray pipe heat-insulating part is the same as the inner diameter of a boss on the inner circumferential surface of the combustion chamber, so that the spray pipe heat-insulating part and the combustion chamber are sealed through a step, and the end face of the front end of the spray pipe heat-insulating part is attached to the end face of a powder column in the combustion chamber. The throat insert 17 is located at the throat of the nozzle insulation 15 and is adhered to the inner surface of the nozzle insulation. And carrying out integrated finish machining after pasting. The heat-insulating part at the front part of the throat insert adopts large arc transition to ensure the flow stability of the fuel gas. A guide section is reserved at the front end of the thread of the spray pipe shell, and when the thread connection is carried out, the thread connection butt joint precision is improved through the guide section, and the thrust deflection numerical value of the connection of the top cover and the combustion chamber is reduced. The length of the guide section is 10 mm.
When the booster is installed, the combustion chamber 3 of the booster is horizontally placed, the threads of the spray pipe 4 and the related matching parts are coated with putty and then assembled at the tail part of the combustion chamber, the igniter 6 is installed on the top cover 2 of the combustion chamber, and the threads of the top cover of the combustion chamber and the matching parts are coated with putty and then assembled at the head part of the combustion chamber; after the booster is assembled, a bottom through hole 9 of the thrust rod 1 is in butt joint fit with a positioning boss 10 of the front top cover 2, the end face of a flange of the thrust rod is in butt joint with the front end face of the top cover of the combustion chamber, and the screw 5 is installed after the rotation angle and the threaded hole are aligned.
According to the invention, the structures of the thrust rod 1 and the front top cover 2 of the booster are improved, so that the connection efficiency of the thrust rod and the front top cover is improved, and the thrust deflection of an engine is reduced.
Claims (7)
1. An unmanned aerial vehicle rocket booster is characterized by comprising a thrust rod, a front top cover, a combustion chamber, a spray pipe, an igniter and a plug; wherein the front top cover is positioned at the front end of the combustion chamber; the central positioning sleeve of the thrust rod is sleeved on the positioning boss at the center of the front top cover, and the end surface of the front end cover is attached to the end surface of the flange plate of the thrust rod; the igniter is positioned in a cavity formed between the inner end surface of the front top cover and the front end surface of the combustion chamber, and one end of the igniter is positioned in the threaded blind hole of the inner end surface of the positioning lug boss of the front top cover; the nozzle and the plug are both in the prior art and assembled according to a conventional method, and the convergent section of the nozzle is installed at the rear end of the combustion chamber through threads; a plug is mounted within the nozzle and is located within the diverging section of the nozzle.
2. A rocket booster for unmanned aerial vehicles as recited in claim 1, wherein said thrust rod is comprised of a central positioning sleeve and a flange plate perpendicular to each other; the inner diameter of the central positioning sleeve is the same as the outer diameter of the positioning boss of the front top cover, and the central positioning sleeve and the positioning boss are in interference fit; the flange plate is evenly provided with connecting holes fixedly connected with the front top cover.
3. A rocket booster for unmanned aerial vehicles as recited in claim 1, wherein said front cap is ellipsoidal; the thickness of the ellipsoid is 3 mm; the outer edge of the outer end face of the front top cover is provided with an annular connecting boss which protrudes axially, and a plurality of threaded holes are uniformly distributed on the boss; a front top cover positioning boss 10 axially protrudes from the center of the outer end surface of the front top cover, and a threaded blind hole for mounting an igniter is formed in the center of the inner end surface of the front top cover positioning boss; the length of the front top cover positioning boss is 15 mm; the annular connecting boss of the front top cover is a stress surface of the front top cover; the outer diameter of the annular connecting boss is 150mm, and the inner diameter of the annular connecting boss is 108 mm.
4. A rocket booster for unmanned aerial vehicles as recited in claim 1, wherein the outer surface of the housing near one end of said front cap is a mating surface with the housing of the combustion chamber; the outer surface of the shell is provided with three steps; in the three-stage steps, the step close to one end of the thrust rod forms a guide section of the combustion chamber shell, and when the threaded connection is carried out, the threaded connection butt joint precision is improved through the guide section, and the thrust deflection numerical value of the connection of the top cover and the combustion chamber is reduced; the length of the guide section is 10 mm; the middle part of the three-stage step is a thread surface connected with the combustion chamber; the step close to the end surface of the near end is a positioning surface matched with the combustion chamber shell to form a positioning spigot; and the surface of the third step is coated with putty of 0.2mm by a conventional method so as to enhance the sealing and heat-insulating effect of the third step.
5. A rocket motor unmanned rocket motor as recited in claim 1, wherein said combustion chamber comprises a combustion chamber housing, grains, a liner, and a thermal insulation layer; the heat insulation layer is adhered to the inner surface of the combustion chamber shell, and a secondary adhered heat insulation layer is arranged on the surface of the heat insulation layer at the matching section of the combustion chamber shell and the front top cover; the surface of the heat insulation layer of the combustion chamber shell and the matching section of the spray pipe is provided with a heat insulation layer which is adhered for the second time; the sealing performance of the combustion chamber shell is improved by the secondary pasting heat insulation layer; a lining layer is sprayed on the surface of the heat insulating layer; the explosive columns are filled in the combustion chamber shell through a charging mould in an adherence pouring mode and are solidified.
6. A rocket motor unmanned aerial vehicle as recited in claim 1, wherein said nozzle comprises nozzle insulation, a nozzle housing, and a throat insert; the spray pipe heat insulation piece is adhered to the inner surface of the spray pipe shell; the throat insert is positioned at the throat of the nozzle insulation and is adhered to the inner surface of the nozzle insulation; the outer diameter of the front end of the spray pipe heat-insulating part is the same as the inner diameter of a boss on the inner circumferential surface of the combustion chamber, so that the spray pipe heat-insulating part and the combustion chamber are sealed by a step, and the end surface of the front end of the spray pipe heat-insulating part is attached to the end surface of a powder column in the combustion chamber; the throat insert is positioned at the throat of the nozzle insulation and is adhered to the inner surface of the nozzle insulation.
7. An unmanned rocket booster as recited in claim 6, wherein the front heat-insulating part of said throat insert is in a large arc transition to ensure the flow stability of the fuel gas; a guide section is reserved at the front end of the thread of the spray pipe shell, and when the threaded connection is carried out, the threaded connection butt joint precision is improved through the guide section, and the thrust deflection numerical value of the connection of the top cover and the combustion chamber is reduced; the length of the guide section is 10 mm.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2020108222778 | 2020-08-16 | ||
| CN202010822277 | 2020-08-16 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112520060A true CN112520060A (en) | 2021-03-19 |
Family
ID=74977236
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110000293.3A Pending CN112520060A (en) | 2020-08-16 | 2021-01-02 | Unmanned aerial vehicle rocket booster |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112520060A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113550841A (en) * | 2021-09-06 | 2021-10-26 | 中国人民解放军战略支援部队航天工程大学 | Gas rocket engine for unmanned aerial vehicle launching and design method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4826104A (en) * | 1986-10-09 | 1989-05-02 | British Aerospace Public Limited Company | Thruster system |
| US20030046923A1 (en) * | 2001-03-08 | 2003-03-13 | Dressler Gordon A. | Pintle injector rocket with expansion-deflection nozzle |
| CN104696104A (en) * | 2013-12-10 | 2015-06-10 | 上海新力动力设备研究所 | Connection structure of blocking ring of solid rocket engine |
| CN109850174A (en) * | 2019-03-08 | 2019-06-07 | 西安爱生技术集团公司 | A kind of rocket assist device of unmanned plane |
| CN110920923A (en) * | 2019-12-23 | 2020-03-27 | 中国人民解放军总参谋部第六十研究所 | Unmanned aerial vehicle launching device with double rocket boosters |
| CN213354875U (en) * | 2020-08-21 | 2021-06-04 | 河南北方红阳机电有限公司 | Unmanned aerial vehicle rocket booster of adjustable thrust |
-
2021
- 2021-01-02 CN CN202110000293.3A patent/CN112520060A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4826104A (en) * | 1986-10-09 | 1989-05-02 | British Aerospace Public Limited Company | Thruster system |
| US20030046923A1 (en) * | 2001-03-08 | 2003-03-13 | Dressler Gordon A. | Pintle injector rocket with expansion-deflection nozzle |
| CN104696104A (en) * | 2013-12-10 | 2015-06-10 | 上海新力动力设备研究所 | Connection structure of blocking ring of solid rocket engine |
| CN109850174A (en) * | 2019-03-08 | 2019-06-07 | 西安爱生技术集团公司 | A kind of rocket assist device of unmanned plane |
| CN110920923A (en) * | 2019-12-23 | 2020-03-27 | 中国人民解放军总参谋部第六十研究所 | Unmanned aerial vehicle launching device with double rocket boosters |
| CN213354875U (en) * | 2020-08-21 | 2021-06-04 | 河南北方红阳机电有限公司 | Unmanned aerial vehicle rocket booster of adjustable thrust |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113550841A (en) * | 2021-09-06 | 2021-10-26 | 中国人民解放军战略支援部队航天工程大学 | Gas rocket engine for unmanned aerial vehicle launching and design method |
| CN113550841B (en) * | 2021-09-06 | 2022-04-12 | 中国人民解放军战略支援部队航天工程大学 | Gas rocket engine for unmanned aerial vehicle launching and design method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109723573B (en) | Double-pulse engine with integrated chemical winding structure and manufacturing method | |
| CN203847275U (en) | Composite propellant engine | |
| CN111810318B (en) | Single-chamber double-thrust solid rocket engine and rocket | |
| CN110145411B (en) | Solid rocket engine inner hole tubular charging structure with inner cavity partition plate and method | |
| CN109595099B (en) | Solid-liquid mixing engine for ground test car experiment | |
| CN202832854U (en) | Combined type heat protective structure in the rear portion of a solid rocket engine combustion chamber | |
| CN106762230A (en) | The non-insert nozzle of solid propellant rocket and manufacture method | |
| CN112520060A (en) | Unmanned aerial vehicle rocket booster | |
| CN103670797A (en) | Solid-liquid scramjet engine | |
| CN109026445B (en) | Multi-nozzle solid attitude control engine blanking cover structure | |
| CN106903901A (en) | For the Low temperature-resistanflexible flexible joint forming method of solid propellant rocket | |
| CN112412658B (en) | Combined core mold with medicine winding function | |
| CN111927652B (en) | Double-pulse solid rocket engine interlayer ablation carbonization controllable experimental device | |
| CN111734553B (en) | Double-pulse engine combustion chamber shell and forming method | |
| CN111222224B (en) | Coating and sleeving design method for freely filling explosive columns in solid rocket engine | |
| CN114683445B (en) | Solid rocket engine disassembly-free wing column type grain forming die and forming method | |
| CN212054925U (en) | Small-size solid rocket engine ignition | |
| JP7098504B2 (en) | Cold spray nozzle and cold spray device | |
| CN112571822B (en) | Memory non-metal core mold structure suitable for winding with medicine and shell forming method | |
| CN113958424B (en) | Rocket boosting engine with inner trajectory curve free of tail warping phenomenon | |
| CN111305973A (en) | Small-size solid rocket engine ignition | |
| CN117052561A (en) | End-combustion solid rocket engine capable of improving mass ratio | |
| CN115962066A (en) | Solid rocket engine and manufacturing method thereof | |
| CN114714545B (en) | Semi-dumbbell-shaped annular groove grain forming die and forming method for solid rocket engine | |
| CN114876673B (en) | Low-cost ablation-resistant embedded spray pipe and processing method thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |