CN110589029B - Solid fuel micro propeller - Google Patents
Solid fuel micro propeller Download PDFInfo
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- CN110589029B CN110589029B CN201910972019.5A CN201910972019A CN110589029B CN 110589029 B CN110589029 B CN 110589029B CN 201910972019 A CN201910972019 A CN 201910972019A CN 110589029 B CN110589029 B CN 110589029B
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- cam
- propellant
- sleeve
- convex part
- solid
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- 239000004449 solid propellant Substances 0.000 title claims abstract description 59
- 239000003380 propellant Substances 0.000 claims abstract description 35
- 238000007599 discharging Methods 0.000 claims abstract description 23
- 238000002347 injection Methods 0.000 claims abstract description 21
- 239000007924 injection Substances 0.000 claims abstract description 21
- 238000002485 combustion reaction Methods 0.000 claims description 13
- 238000003756 stirring Methods 0.000 claims description 6
- 239000007921 spray Substances 0.000 claims description 3
- 238000000034 method Methods 0.000 claims 1
- 239000000463 material Substances 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 239000007787 solid Substances 0.000 description 4
- 230000010354 integration Effects 0.000 description 3
- 229910010293 ceramic material Inorganic materials 0.000 description 2
- 238000005192 partition Methods 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
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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
- B64G1/402—Propellant tanks; Feeding propellants
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transmission Devices (AREA)
Abstract
The invention relates to the field of propellers, in particular to a solid fuel micro propeller. A solid fuel micro-thruster, comprising: the device comprises a shell, a stepping motor, a solid propellant storage box, a screw, a propellant discharging device and an injection pipe; the stepping motor is arranged inside the shell, one end of the screw is connected with the stepping motor, and the propellant discharging device in the solid propellant storage box at the other end of the screw is fixedly connected; the propellant goes out case device includes: the connecting rod comprises a sleeve, a connecting part, a first cam, a second cam and a connecting rod. The invention solves the problems that the existing propeller has poor repeatable propulsion performance and can only realize single-point single propulsion.
Description
Technical Field
The invention relates to the field of propellers, in particular to a solid fuel micro propeller.
Background
The micro-propulsion system has the characteristics of high integration degree, small volume, light weight, high response speed, high specific impulse, high reliability, easiness in integration into a propulsion array and the like, and has wide application prospects in the aspects of attitude and track control, deep space exploration and the like of the spacecraft.
At present, in micro propellers researched at home and abroad, the micro cold air propeller has large volume, high quality and small specific impulse; the micro-electric thruster has the advantages of high reliability, simple and compact structure, capability of providing accurate and adjustable impulse, easiness in system integration and the like. The working principle of the solid micro-thruster is that after the solid micro-thruster is electrified, the firing resistor is heated to ignite the solid propellant, and the gas pressure generated by the combustion of the solid propellant generates thrust, so that the spacecraft and the like are pushed to realize orbital transfer and movement.
The existing solid micro-propeller has the problems of poor repeatable propelling performance and capability of realizing single-point single propelling.
Disclosure of Invention
Accordingly, the present invention has been made in view of the above problems, and it is an object of the present invention to provide a solid fuel micro-thruster capable of precisely controlling the amount of a solid propellant by providing the amount of the solid propellant in advance according to the propulsion power required by a satellite.
In one aspect of the invention, a solid fuel micro-thruster comprises: the device comprises a shell, a stepping motor, a solid propellant storage box, a screw, a propellant discharging device and an injection pipe;
the stepping motor is arranged inside the shell, one end of the screw is connected with the stepping motor, and the propellant discharging device in the solid propellant storage box at the other end of the screw is fixedly connected;
the propellant goes out case device includes: the connecting device comprises a sleeve, a connecting part, a first cam, a second cam and a connecting rod;
a feed port is formed in the wall surface of the sleeve, a stirring block is arranged on one side of the feed port, and the sleeve is coaxially fixed with the end part of the screw rod through a connecting part;
one side of a first cam bulge is linear, the other side of the first cam bulge has a certain radian, the first cam is attached to the inner wall of the sleeve, and a spring is arranged between the end part of the first cam and the connecting part;
the second cam and the first cam are coaxially arranged in a mirror image mode, the boss of the second cam is matched with the boss of the first cam, and a first baffle is arranged in the second cam;
the connecting rod is positioned in the sleeve, one end of the connecting rod penetrates through the first cam and is fixedly connected with the connecting part, the other end of the connecting rod is provided with a second baffle, and the second baffle is matched with the first baffle to seal the inner diameter of the second cam;
and the port of the injection pipe is connected with a second cam, and one end of the second cam, which is close to the second cam, is provided with a grid.
In another aspect of the invention, a solid fuel micro-thruster includes: the device comprises a stepping motor, a solid propellant storage box, a screw, a propellant discharging device, a combustion chamber, an electromagnetic valve and an injection pipe;
the stepping motor is arranged at one end of the solid propellant storage tank;
one end of the screw rod is connected with the stepping motor, and the other end of the screw rod extends into the solid propellant storage box;
the propellant goes out case device includes: the connecting rod is connected with the connecting part;
the sleeve is coaxially fixed with the end part of the screw rod through a connecting part, a feed port is arranged on the wall surface of the sleeve, and a stirring block is arranged on one side of the feed port;
one side of a convex part of the first cam is linear, the other side of the convex part of the first cam has a certain radian, the first cam is arranged in the sleeve, the outer side of the first cam is attached to the inner wall of the sleeve, a spring is connected between the first cam and the connecting part, and a push rod is arranged on the inner diameter of the first cam and is longer than the convex part of the first cam;
the connecting rod is positioned in the sleeve, and one end of the connecting rod penetrates through the first cam and is fixed with the axis of the connecting part;
the convex part of the second cam and the convex part of the first cam are coaxially arranged in a mirror image manner;
the valve consists of two semicircular blocks and is connected with two ports of the cam through a torsion spring;
the number of the injection pipes is three, the injection pipes are arranged along an X axis, a Y axis and a Z axis and are communicated with the combustion chamber through pipes, and electromagnetic valves are arranged at the pipeline joints of the combustion chamber and the injection pipes;
a solid fuel micro-thruster, comprising: the device comprises a rack, a storage bin, a first motor, a transmission belt, a second motor, a closing door, a first thimble and a control circuit board.
The invention has the advantages of
The invention pushes the fixed propellant to move to the propellant box discharging device through the rotation of the screw rod, and then intermittently sprays the fixed propellant through the propellant box discharging device, thereby being capable of controlling the attitude of the satellite to adjust the dosage of the solid propellant required each time, realizing the repeated propelling of the solid micro-propeller, and simultaneously controlling the moving-out frequency of the solid propellant through the propellant box discharging device until stopping through controlling the rotation speed of the screw rod, thereby being capable of enabling the satellite to slowly finish the action.
Drawings
Fig. 1 is a schematic overall structure diagram of a first embodiment of the present invention.
Fig. 2 is an exploded view of a propellant dispenser according to a first embodiment of the present invention.
Fig. 3 is a schematic diagram of the movement of the screw according to the first embodiment of the present invention.
Fig. 4 is a schematic diagram of the movement of the propellant out-of-box apparatus of the first embodiment of the present invention.
Fig. 5 is a schematic overall structure diagram of a second embodiment of the present invention.
Fig. 6 is an exploded view of a discharging device according to a second embodiment of the present invention.
FIGS. 1-4 show: the device comprises a shell 1, a stepping motor 2, a solid propellant storage tank 3, a screw 4, a propellant 5 discharging device 6, a spray pipe 51, a sleeve 52, a connecting part 53, a cam I54, a cam II 55, a connecting rod 511, a feed inlet 511, a material stirring block 512, a spring 531, a baffle I541 and a baffle II 551.
FIGS. 5-6 show: 1-1-stepping motor, 2-1-solid propellant storage box, 3-1-screw, 4-1-propellant discharging device, 5-1-combustion chamber, 6-1-solenoid valve, 7-1-injection pipe, 41-1-sleeve, 42-1-connecting part, 43-1-cam I, 44-1-connecting rod, 45-1-cam II, 46-1-valve, 411-1-feeding hole, 412-1-material pulling block, 431-1 spring and 432-1-push rod.
Detailed Description
The present invention is further illustrated in the following description with reference to specific embodiments and the accompanying drawings, wherein the details are set forth in order to provide a thorough understanding of the present invention, but it is apparent that the present invention can be embodied in many other forms different from the description herein, and it will be readily appreciated by those skilled in the art that the present invention can be embodied in many different forms without departing from the spirit and scope of the invention.
The first embodiment: as shown in fig. 1, the solid fuel micro-thruster includes: the device comprises a shell 1, a stepping motor 2, a solid propellant storage tank 3, a screw rod 4, a propellant discharging device 5 and an injection pipe 6;
two partition plates are arranged in the shell 1, and a solid propellant storage tank 3 is formed in the space between the two partition plates;
the stepping motor 2 is arranged in the shell 1 and is positioned at one end of the solid propellant storage tank 3;
one end of the screw rod 4 is connected with the stepping motor 2, and the other end of the screw rod extends into the solid propellant storage box 3;
as shown in fig. 2, the propellant out-of-box device 5 comprises: the sleeve 51, the connecting part 52, the first cam 53, the second cam 54 and the connecting rod 55;
the sleeve 51 is positioned in the solid propellant storage box 3, the sleeve 51 is coaxially fixed with the end part of the screw rod 4 through the connecting part 52, a feeding hole 511 is formed in the wall surface of the sleeve 51, and a material stirring block 512 is arranged on one side of the feeding hole 511;
the first cam 53 is made of ceramic materials, high-temperature-resistant rubber is arranged on the outer diameter of the first cam 53, one side of a convex part of the first cam 53 is linear, and the other side of the convex part has a certain radian;
the first cam 53 is arranged in the sleeve 51, the high-temperature-resistant rubber is attached to the inner wall of the sleeve 51, the first initial cam 53 is positioned on one side of the feed port 511, which is close to the connecting part 52, and a spring 531 is connected between the first cam 53 and the connecting part 52;
the second cam 54 is fixed at the other end of the solid propellant storage box 3, the convex part of the second cam 54 extends into the solid propellant storage box 3, wherein the shape of the convex part of the second cam 54 is the same as that of the convex part of the first cam 53, the second cam 54 and the first cam 53 are arranged in a mirror image mode, the inner diameter of the second cam 54 is provided with a first baffle 541, and the initial second cam 54 is abutted against the convex part of the first cam 53;
the connecting rod 55 is a rectangular rod and is positioned in the sleeve 51, wherein one end of the connecting rod 55 penetrates through the first cam 53 and is fixed with the axis of the connecting part 52, and the other end of the connecting rod 55 is provided with a second baffle 551;
the second baffle 551 and the first baffle 541 close the inner diameter of the second cam 54, wherein high-temperature-resistant rubber is arranged at the joint of the second baffle 551 and the inner diameter of the second cam 54;
the port of the injection pipe 6 is connected with the second cam 54, wherein an igniter is arranged at the joint of the injection pipe 6 and the second cam 54, and a grid (not shown) is arranged at one end of the injection pipe 6 close to the second cam 54 and used for blocking the fixed propellant from directly escaping to the space.
The working principle of the first embodiment of the invention is as follows:
when the satellite needs to adjust the attitude or orbit control, the corresponding solid propellant is provided by setting the rotation number of the screw rod 4 in advance according to the propelling power required by the satellite, so that the using amount of the solid propellant is accurately controlled, as shown in fig. 3, firstly, the stepping motor 2 drives the screw rod 4 to rotate, the screw rod 4 propels the solid propellant to move towards the propellant box discharging device 5, the propellant box discharging device 5 rotates along with the screw rod 4, the poking block 512 propels the solid propellant into the sleeve 51 along the feed inlet 511, meanwhile, the first cam 53 is separated from the convex part of the second cam 54, as shown in fig. 4, the first cam 53 is ejected along the linear side of the convex part of the second cam 54 through the spring 531, the first baffle 541 is overlapped with the second baffle 551, the inner diameter of the second cam 54 is opened, the first cam 53 ejects the fixed propellant, and the first cam 53 seals the feed inlet 511, the, the generated high-pressure high-temperature gas is sprayed out along the spraying pipe 6 to move the satellite, and when the satellite movement is close to ending, the stepping motor 2 slows down the rotating speed to control the moving-out frequency of the solid propellant until the satellite movement is stopped, so that the satellite can slowly end the movement.
Second embodiment: as shown in fig. 5, the solid fuel micro-thruster includes: 1-1 parts of a stepping motor, 2-1 parts of a solid propellant storage tank, 3-1 parts of a screw, 4-1 parts of a propellant discharging device, 5-1 parts of a combustion chamber, 6-1 parts of an electromagnetic valve and 7-1 parts of an injection pipe;
the stepping motor 1-1 is arranged at one end of the solid propellant storage tank 2-1;
one end of the screw 3-1 is connected with the stepping motor 1-1, and the other end of the screw extends into the solid propellant storage tank 2-1;
as shown in fig. 6, the propellant out-of-box apparatus 4-1 comprises: the connecting device comprises a sleeve 41-1, a connecting part 42-1, a first cam 43-1, a connecting rod 44-1, a second cam 45-1 and a valve 46-1;
the sleeve 41-1 is positioned in the solid propellant storage box 2-1, the sleeve 41-1 is coaxially fixed with the end part of the screw rod 3-1 through the connecting part 42-1, a feeding hole 411-1 is formed in the wall surface of the sleeve 41-1, and a material stirring block 412-1 is arranged on one side of the feeding hole 411-1;
the first cam 43-1 is made of ceramic materials, high-temperature-resistant rubber is arranged on the outer diameter of the first cam 43-1, one side of a convex part of the first cam 43-1 is linear, and the other side of the convex part has a certain radian;
the first cam 43-1 is arranged in the sleeve 41-1, the high-temperature-resistant rubber is attached to the inner wall of the sleeve 41-1, the first initial cam 43-1 is positioned on one side of the discharge port 411-1, which is close to the connecting part 42-1, and a spring 431-1 is connected between the first cam 43-1 and the connecting part 42-1, wherein a push rod 432-1 is arranged on the inner diameter of the first cam 43-1, and the push rod 432-1 is longer than a convex part of the first cam 43-1;
the connecting rod 44-1 is a rectangular rod and is positioned inside the sleeve 41-1, wherein one end of the connecting rod 44-1 penetrates through the first cam 43-1 and is fixed with the axis of the connecting part 42-2;
the second cam 45-1 is fixed at the other end of the solid propellant storage tank 2-1, and a convex part of the second cam 45-1 extends into the solid propellant storage tank 2-1, wherein the second cam 45-1 and the first cam 43-1 are in the same convex part shape, and the second cam 45-1 and the first cam 43-1 are arranged in a mirror image mode;
the valve 46-1 consists of two semicircular blocks and is connected with the port of the second cam 45-1 through a torsion spring, and the two semicircular blocks of the valve 46-1 seal the inner diameter of the second cam 45-1 when abutting against each other;
the combustion chamber 5-1 is communicated with the second cam 45-1, and an igniter is arranged in the combustion chamber 5-1;
the number of the injection pipes 7-1 is three, the injection pipes are arranged along an X axis, a Y axis and a Z axis and are communicated with the combustion chamber 5-1 through pipes, and the electromagnetic valve 6-1 is arranged at the pipeline joint of the combustion chamber 5-1 and the injection pipe 7-1.
The working principle of the second embodiment of the present invention:
when the attitude or orbit of the satellite needs to be adjusted, the corresponding solid propellant is provided by setting the number of rotation turns of the screw 3-1 according to the propelling power needed by the satellite in advance, so that the using amount of the solid propellant is accurately controlled, firstly, the screw 3-1 is driven by the stepping motor 1-1 to rotate, the screw 3-1 pushes the solid propellant to move towards the propellant box discharging device 4-1, the propellant box discharging device 4-1 rotates along with the screw 3-1, the solid propellant is pushed into the sleeve 41-1 along the feeding hole 411-1 by the material poking block 412-1, meanwhile, the first cam 43-1 is separated from the convex part of the second cam 45-1, and the first cam 43-1 and the second cam 45-1 are ejected from the linear side of the convex part through the spring 431-1, the push rod 432-1 pushes the valve 46-1 open, the inner diameter of the cam II 45-1 is opened, the cam I43-1 ejects solid propellant, the cam I43-1 seals the feed inlet 411-1, the solid propellant enters the combustion chamber 5-1, the igniter ignites solid fuel, the electromagnetic valve 6-1 is opened, generated high-pressure high-temperature gas is sprayed out along the injection pipe 7-1 to move a satellite, the electromagnetic valve 6-1 controls the flow of the high-pressure high-temperature gas, the other electromagnetic valve 6-1 is opened, the thrust forces of the two propulsion pipelines 7-1 are mutually offset, the satellite is decelerated and then positioned, and the stepping motor 1-1 is decelerated at the same time to slow down the rotating speed so as to control the moving-out frequency of the solid propellant until the satellite stops, so that the using.
Claims (3)
1. A solid fuel micro-thruster, comprising: the device comprises a shell (1), a stepping motor (2), a solid propellant storage box (3), a screw (4), a propellant discharging device (5) and an injection pipe (6);
the method is characterized in that: the stepping motor (2) is arranged in the shell (1), one end of the screw rod (4) is connected with the stepping motor (2), the other end of the screw rod (4) is fixedly connected with a propellant box discharging device (5) in the solid propellant storage box (3), the propellant box discharging device (5) intermittently sprays the solid propellant, the propellant box discharging device (5) is connected with the jet pipe (6), and one end, close to the propellant box discharging device (5), of the jet pipe (6) is provided with a grid;
the propellant out-of-box device (5) comprises: the device comprises a sleeve (41-1), a connecting part (42-1), a first cam (43-1), a connecting rod (44-1), a second cam (45-1) and a valve (46-1);
the propellant box discharging device (5) rotates along with the screw (4), meanwhile, the first cam (43-1) is separated from the convex part of the second cam (45-1), the first cam (43-1) and the linear side of the convex part of the second cam (45-1) are ejected through the spring (431-1), the push rod (432-1) pushes the valve (46-1) open, the first cam (43-1) ejects solid propellant, and the first cam (43-1) blocks the feed inlet (411-1).
2. The solid fuel micro-thruster of claim 1, wherein: the sleeve (41-1) is coaxially fixed with the end part of the screw rod through a connecting part (42-1), wherein a feed port (411-1) is formed in the wall surface of the sleeve (41-1), and a stirring block (412-1) is arranged on one side of the feed port (411-1);
one side of the convex part of the first cam (43-1) is linear, the other side of the convex part has a certain radian, the first cam (43-1) is arranged in the sleeve (41-1), the outer side of the first cam is attached to the inner wall of the sleeve (41-1), a spring (431-1) is connected between the first cam (43-1) and the connecting part (42-1), a push rod (432-1) is arranged on the inner diameter of the first cam (43-1), and the push rod (432-1) is longer than the convex part of the first cam (43-1);
the connecting rod (44-1) is positioned in the sleeve (41-1), and one end of the connecting rod penetrates through the cam I (43-1) and is fixed with the axis of the connecting part (42-1);
the convex part of the second cam (45-1) and the convex part of the first cam (43-1) are coaxially arranged in a mirror image manner;
the valve (46-1) is composed of two semicircular blocks and is connected with the port of the second cam (45-1) through a torsion spring.
3. The solid fuel micro-thruster of claim 1, wherein: the propellant box outlet device (5) is connected with three injection pipes, the three injection pipes are distributed along an X axis, a Y axis and a Z axis and communicated with a combustion chamber (5-1) through pipes, and electromagnetic valves (6-1) are arranged at the joints of the combustion chamber (5-1) and the injection pipes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910972019.5A CN110589029B (en) | 2019-10-18 | 2019-10-18 | Solid fuel micro propeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910972019.5A CN110589029B (en) | 2019-10-18 | 2019-10-18 | Solid fuel micro propeller |
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| Publication Number | Publication Date |
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| CN110589029A CN110589029A (en) | 2019-12-20 |
| CN110589029B true CN110589029B (en) | 2020-09-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910972019.5A Active CN110589029B (en) | 2019-10-18 | 2019-10-18 | Solid fuel micro propeller |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112124634B (en) * | 2020-09-07 | 2023-12-22 | 兰州空间技术物理研究所 | Micro-flow storage and supply device for colloid propeller |
| CN113353295A (en) * | 2021-06-29 | 2021-09-07 | 杨德安 | Solid fuel space capsule |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002332000A (en) * | 2001-05-10 | 2002-11-19 | Mitsubishi Heavy Ind Ltd | Ppt propellant supply mechanism |
| JP2002357298A (en) * | 2001-06-04 | 2002-12-13 | Mitsubishi Heavy Ind Ltd | Screwed joint for pressure vessel |
| CN201972812U (en) * | 2011-02-24 | 2011-09-14 | 西北工业大学 | Miniature solid rocket engine |
| CN108488005A (en) * | 2018-02-13 | 2018-09-04 | 重庆大学 | A kind of multiple-pulse solid propellant rocket of thrust controllable |
| CN110284995A (en) * | 2019-06-14 | 2019-09-27 | 北京理工大学 | A kind of disk transfer type locellus solid propellant rocket |
-
2019
- 2019-10-18 CN CN201910972019.5A patent/CN110589029B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002332000A (en) * | 2001-05-10 | 2002-11-19 | Mitsubishi Heavy Ind Ltd | Ppt propellant supply mechanism |
| JP2002357298A (en) * | 2001-06-04 | 2002-12-13 | Mitsubishi Heavy Ind Ltd | Screwed joint for pressure vessel |
| CN201972812U (en) * | 2011-02-24 | 2011-09-14 | 西北工业大学 | Miniature solid rocket engine |
| CN108488005A (en) * | 2018-02-13 | 2018-09-04 | 重庆大学 | A kind of multiple-pulse solid propellant rocket of thrust controllable |
| CN110284995A (en) * | 2019-06-14 | 2019-09-27 | 北京理工大学 | A kind of disk transfer type locellus solid propellant rocket |
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| CN110589029A (en) | 2019-12-20 |
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Effective date of registration: 20231219 Address after: 615000, 6th floor, Building 3, Nantan Resettlement Community, No. 99 Hedong Avenue, Xichang City, Liangshan Yi Autonomous Prefecture, Sichuan Province Patentee after: Xichang Satellite Technology Co.,Ltd. Address before: 518000 room 116, building 7, spark online project, No.2, Wuhe South Road, Bantian street, Longgang District, Shenzhen City, Guangdong Province Patentee before: Shenzhen Magic Cube Satellite Technology Co.,Ltd. |
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