CN114543600A - 40 mm pneumatic steering engine system with air source - Google Patents
40 mm pneumatic steering engine system with air source Download PDFInfo
- Publication number
- CN114543600A CN114543600A CN202210167500.9A CN202210167500A CN114543600A CN 114543600 A CN114543600 A CN 114543600A CN 202210167500 A CN202210167500 A CN 202210167500A CN 114543600 A CN114543600 A CN 114543600A
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- China
- Prior art keywords
- steering engine
- rudder wing
- pneumatic
- rudder
- compressed air
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- 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.)
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Links
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims abstract description 41
- 230000007246 mechanism Effects 0.000 claims abstract description 36
- 239000007789 gas Substances 0.000 claims abstract description 28
- 230000007704 transition Effects 0.000 claims abstract description 25
- 238000006243 chemical reaction Methods 0.000 claims abstract description 22
- 229910052757 nitrogen Inorganic materials 0.000 claims abstract description 21
- 230000005540 biological transmission Effects 0.000 claims abstract description 18
- 230000004044 response Effects 0.000 claims abstract description 13
- 238000010586 diagram Methods 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- QJGQUHMNIGDVPM-UHFFFAOYSA-N nitrogen group Chemical group [N] QJGQUHMNIGDVPM-UHFFFAOYSA-N 0.000 description 1
- 238000005381 potential energy Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/01—Arrangements thereon for guidance or control
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
- F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/60—Steering arrangements
- F42B10/62—Steering by movement of flight surfaces
- F42B10/64—Steering by movement of flight surfaces of fins
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention discloses a 40 mm pneumatic steering engine system with an air source, which takes high-pressure nitrogen as working energy, controls a rudder wing to deflect in a high-speed response to a control instruction of a missile, is matched with a 40 mm microminiature smart missile, controls the posture and the flight direction of the missile by utilizing the aerodynamic force generated by the high-pressure nitrogen during flight, and enables the missile to fly along a specified trajectory, a compressed air transition cavity is used for storing high-pressure gas released in a combined high-pressure gas cylinder, an overflow valve is used for keeping constant air pressure in the compressed air transition cavity, a rudder wing transmission mechanism is connected with a corresponding rudder wing, a driver is electrically connected with a pneumatic conversion device, the pneumatic conversion device is controlled by the driver to release the high-pressure gas in the compressed air transition cavity into a cylinder body where a piston body is located, and the piston body pushes the rudder wing transmission mechanism to move to drive the rudder wing to rotate around a locking pin, the attitude and flight direction of the missile are changed.
Description
Technical Field
The invention discloses a 40 mm pneumatic steering engine system with an air source, belongs to the technical field of guided missile guidance steering engines, and particularly relates to a microminiature electromechanical system which is controlled by a cold air type pneumatic steering engine with an air source and enables a missile to fly along a specified trajectory.
Background
The smart guided ammunition with the diameter of 40 mm (the current international minimum-diameter missile system) has the most important characteristics of small appearance volume, low cost and guidance capability. The requirements on a steering engine which is one of main components of a control system are the characteristics of high response, small volume, small electromagnetic interference, strong adaptability to the whole missile and the like.
The two control schemes can be adopted at present, namely a steering engine system adopts a scheme of a brushless motor and a gear reduction mechanism or is directly driven by a linear motor, and the two schemes have the main defects of being restricted by a narrow space on the aspect of elasticity, and in the engineering design process, the power density of a direct-current brushless motor is too high and exceeds the technical requirement of the existing electromagnetic material, and the control response characteristic is slow; the deflection torque of the rudder wing of the steering engine completely depends on the torque output by the motor, the frequent forward and reverse conversion of the motor has large working current, the power requirement on the whole power supply of the missile is high, the working time of the power supply arranged in a specified narrow space is short, the electromagnetic interference on other control parts is large, and the range and the working reliability of the missile are influenced. Under the influence, the caliber of the existing micro missile is larger than 40 mm.
Disclosure of Invention
The invention overcomes the defects of the prior art, provides a 40 mm pneumatic steering engine system with an air source, takes high-pressure nitrogen as working energy, controls the deflection of a rudder wing by responding to the control instruction of a missile at high speed, is matched with a 40 mm microminiature smart missile, and controls the posture and the flight direction of the missile by utilizing the aerodynamic force generated by the high-pressure nitrogen during flight so as to ensure that the missile flies along the specified trajectory.
In order to solve the technical problems, the invention adopts the technical scheme that: a40 mm pneumatic steering engine system with an air source comprises a steering engine, a rudder wing and a spring unfolding mechanism, wherein the rudder wing is hinged in the steering engine through a locking pin, the spring unfolding mechanism is arranged in the steering engine, one end of the spring unfolding mechanism is connected to the rudder wing, the other end of the spring unfolding mechanism is arranged in the steering engine, the rudder wing can be contracted in the steering engine in a non-working state, the pneumatic steering engine system further comprises a driver, a rudder wing transmission mechanism, a pneumatic conversion device, an overflow valve, a combined high-pressure air bottle, a compressed air transition cavity and a piston body, the outer diameter of the steering engine is 40 mm, the combined high-pressure air bottle is arranged in the steering engine, the compressed air transition cavity is arranged on the air outlet side of the combined high-pressure air bottle and used for storing high-pressure air released in the combined high-pressure air bottle, and the overflow valve is arranged on the compressed air transition cavity, the overflow valve is used for keeping constant air pressure in the compressed air transition cavity, the piston bodies are arranged in parallel to the axial direction of the steering engine, the cylinder body where each piston body is located and the compressed air transition cavity are communicated through a pneumatic conversion device, the action end of each piston body is connected with a rudder wing transmission mechanism, the rudder wing transmission mechanism is connected with the corresponding rudder wing, the driver is arranged at the tail of the steering engine, the driver is electrically connected with the pneumatic conversion device, the pneumatic conversion device is controlled through the driver to release high-pressure air in the compressed air transition cavity into the cylinder body where the piston body is located, and the piston body pushes the rudder wing transmission mechanism to move to drive the rudder wing to rotate around the locking pin so as to change the posture and the flying direction of the missile.
The pneumatic switching device is an electromagnetic valve, and the response time of the dynamic characteristic of the electromagnetic valve is less than or equal to 6 milliseconds.
The high-pressure gas in the combined high-pressure gas cylinder is nitrogen, and the nitrogen amount in the combined high-pressure gas cylinder can meet the requirement that a cylinder body where the piston body is located works for more than 20 seconds.
Compared with the prior art, the invention has the following beneficial effects.
First, the structure of the invention is designed in a miniaturized shape, the external dimension is 40 mm in diameter and 85 mm in length, and the invention can be directly applied to a smart guided ammunition weapon system with the diameter of 40 mm.
Secondly, the dynamic characteristic of the invention achieves that the response time is less than or equal to 6 milliseconds, the output torque is more than 0.01 nm, and the control characteristic of a smart guided ammunition weapon system with the caliber of 40 mm can be greatly provided.
Thirdly, the effective working time of the invention is improved to more than 20 seconds, the adaptability to matching is stronger, and the invention can be matched with other missile platforms except the smart guided ammunition weapon system with the caliber of 40 mm.
Fourthly, the missile power supply system has working energy, reduces the power requirement on the missile power supply, and simplifies the overall design difficulty of the missile.
Drawings
The invention is further described below with reference to the accompanying drawings.
FIG. 1 is a schematic structural diagram of the present invention.
Fig. 2 is a side view of the present invention.
Fig. 3 is a structural schematic diagram of the unfolding of the rudder wing according to the embodiment of the present invention.
FIG. 4 is a schematic structural diagram of the contraction of the rudder wing according to the embodiment of the present invention.
In the figure: the device comprises a driver 1, a rudder wing 2, a rudder wing transmission mechanism 3, a pneumatic conversion device 4, an overflow valve 5, a combined high-pressure gas cylinder 6, a compressed air transition cavity 7, a spring unfolding mechanism 8 and a piston body 9.
Detailed Description
As shown in fig. 1 to 4, the 40 mm pneumatic steering engine system with an air source comprises a steering engine, a rudder wing 2 and a spring unfolding mechanism 8, wherein the rudder wing 2 is hinged in the steering engine through a locking pin, the spring unfolding mechanism 8 is positioned in the steering engine, one end of the spring unfolding mechanism 8 is connected to the rudder wing 2, the other end of the spring unfolding mechanism 8 is arranged in the steering engine, the rudder wing 2 can be contracted in the steering engine in a non-working state, the pneumatic steering engine system further comprises a driver 1, a rudder wing transmission mechanism 3, a pneumatic conversion device 4, an overflow valve 5, a combined high-pressure air cylinder 6, a compressed air transition cavity 7 and a piston body 9, the outer diameter of the steering engine is 40 mm, the combined high-pressure air cylinder 6 is arranged in the steering engine, the compressed air transition cavity 7 is arranged on the side of an air outlet of the combined high-pressure air cylinder 6, and the compressed air transition cavity 7 is used for storing high-pressure air released in the combined high-pressure air cylinder 6, the compressed air transition cavity 7 is provided with an overflow valve 5, the overflow valve 5 is used for keeping constant air pressure in the compressed air transition cavity 7, the plurality of piston bodies 9 are arranged in parallel to the steering engine axial direction, the cylinder body where each piston body 9 is located is communicated with the compressed air transition cavity 7 through a pneumatic conversion device 4, the action end of each piston body 9 is connected with a rudder wing transmission mechanism 3, the rudder wing transmission mechanism 3 is connected with the corresponding rudder wing 2, the driver 1 is arranged at the tail part of the steering engine, the driver 1 is electrically connected with the pneumatic conversion device 4, the driver 1 controls the pneumatic conversion device 4 to release the high-pressure air in the compressed air transition cavity 7 into the cylinder body in which the piston body 9 is positioned, the piston body 9 pushes the rudder wing transmission mechanism 3 to move so as to drive the rudder wing 2 to rotate around the locking pin, and the posture and the flight direction of the missile are changed.
The pneumatic switching device 4 is an electromagnetic valve, and the response time of the dynamic characteristic of the electromagnetic valve is less than or equal to 6 milliseconds.
The high-pressure gas in the combined high-pressure gas cylinder 6 is nitrogen, and the nitrogen amount in the combined high-pressure gas cylinder 6 can meet the requirement that the cylinder body where the piston body 9 is located works for more than 20 seconds.
The driver 1 of the invention is internally provided with a battery for driving the electromagnetic valve to operate.
The invention adopts the high response characteristic design of the microminiature pneumatic steering engine control, the response time is less than or equal to 6 milliseconds, and the output torque is more than 0.01 nm.
The invention adopts the design of micro-miniature appearance volume, and arranges the combined high-pressure gas cylinder, the safety valve, the rudder wing deflection mechanism, the pneumatic actuating device, the rudder wing opening and locking mechanism, the driving circuit, the full-elastic butt joint interface and other components in a narrow space with the diameter of 40 mm and the length of 85 mm.
According to the invention, the steering engine deflection working output torque adopts nitrogen stored in a high-pressure gas cylinder as a working gas source, only the control circuit and the electromagnetic valve consume current, the required current is small, the requirement on the power supply power of the missile is low, and the electromagnetic interference on other parts is small.
The micro-leakage pneumatic switching device is adopted, the self-contained air source is efficiently utilized, and the effective working time of the steering engine is effectively prolonged to be more than 20 seconds.
The folding rudder wing unfolding mode of the invention adopts a spring unfolding mechanism to directly push the rudder wing to rotate the rudder wing 90 degrees in place along a rotating shaft, and the lock pin is locked to prevent the rudder wing from rebounding and vibrating, thereby completing the function of stably unfolding the rudder wing.
The invention relates to a microminiature electromechanical system which takes high-pressure nitrogen as working energy, controls a rudder wing to deflect in a high-speed response mode according to a control instruction of a missile, is matched with a 40-millimeter microminiature smart missile to generate aerodynamic force for flying, controls the posture and the flying direction of the missile, and enables the missile to fly along a specified trajectory.
The invention relates to a cold air type pneumatic steering engine system with energy sources, which is mainly applied to the guidance flight control of smart guidance ammunition with a small diameter of 40 millimeters.
The combined type high-pressure gas cylinder, the micro-leakage pneumatic conversion device, the overflow valve, the rudder wing transmission mechanism, the driving circuit and other components are integrated into a narrow space with the diameter of 40 mm and the length of 85 mm after being miniaturized, and the combined type high-pressure gas cylinder has the following advantages:
1. the design of miniaturization layout, the microminiaturization design of components such as combined high-pressure gas bomb, the micro-leakage pneumatic conversion device, the drive circuit, the rudder wing transmission mechanism, the overflow valve and the like are integrated into a narrow space with the diameter of 40 mm and the length of 85 mm.
2. The micro-leakage pneumatic conversion device improves the air source utilization rate of the cold air type pneumatic steering engine to more than 85 percent and improves the effective working time of the steering engine to more than 20 seconds.
3. The comprehensive dynamic characteristic of the miniaturized steering engine achieves that the response time is less than or equal to 6 milliseconds, and the output torque is greater than 0.01 nm.
4. From cold air formula pneumatic steering wheel system who takes working air supply, reduce the power requirement to power on the bullet
The present invention will be further described with reference to the following detailed description.
In the embodiment, nitrogen stored in the combined high-pressure gas cylinder 6 is used as a gas source, and high-pressure nitrogen is used as an energy source, and a double-channel (can be designed into three channels according to the requirements of a control system) three-position rudder control mode is adopted. The combined high-pressure gas cylinder 6 outputs high-pressure nitrogen, the high-pressure nitrogen is provided to the compressed air transition cavity 7 after being decompressed, certain pressure is kept, the overflow valve 5 is designed to overflow overpressure nitrogen, and stable working pressure is guaranteed to be provided for the high-pressure nitrogen 6.
In the embodiment, when the steering engine is in a non-working state, the rudder wings 2 are folded into the rudder cabin, after the missile is launched, the spring unfolding mechanism 8 enables the rudder wings 2 to be unfolded out of the steering engine cabin and reliably locked in place, and the steering engine is switched to a working state.
In the embodiment, the pneumatic conversion device 4 uses nitrogen as a working energy source to convert the compression potential energy of the nitrogen into the mechanical kinetic energy of the piston. The driver 1 controls the pneumatic conversion device 4 to enable the nitrogen to push the piston to reciprocate at a high speed according to the on-missile control instruction, the piston pushes the rudder wing transmission mechanism 3 to deflect and drive the rudder wing 2 to output torque, the response time of the dynamic characteristic of the steering engine is less than or equal to 6 milliseconds, and the output torque is greater than 0.01 nm, so that the problems of high response and high output torque characteristic of a steering engine component are solved.
In the embodiment, the power consumption of the steering engine driver and the electromagnet is low, and no large current impact is generated on the missile circuit and the power supply, so that the problems of electromagnetic interference and large current impact on the missile circuit are solved.
The embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited to the above embodiments, and various changes can be made within the knowledge of those skilled in the art without departing from the gist of the present invention.
Claims (3)
1. A40 mm pneumatic steering engine system with an air source comprises a steering engine, a rudder wing (2) and a spring unfolding mechanism (8), wherein the rudder wing (2) is hinged in the rudder engine through a locking pin, the spring unfolding mechanism (8) is positioned in the rudder engine, one end of the spring unfolding mechanism (8) is connected to the rudder wing (2), the other end of the spring unfolding mechanism (8) is arranged in the steering engine, the rudder wing (2) can be contracted in the steering engine in a non-working state, the pneumatic steering engine system is characterized by further comprising a driver (1), a rudder wing transmission mechanism (3), a pneumatic conversion device (4), an overflow valve (5), a combined high-pressure air cylinder (6), a compressed air transition cavity (7) and a piston body (9), the outer diameter of the steering engine is 40 mm, the combined high-pressure air cylinder (6) is arranged in the rudder engine, and a compressed air transition cavity (7) is arranged on the air outlet side of the combined high-pressure air cylinder (6), the compressed air transition cavity (7) is used for storing high-pressure gas released in the combined high-pressure gas cylinder (6), an overflow valve (5) is arranged on the compressed air transition cavity (7), the overflow valve (5) is used for keeping constant air pressure in the compressed air transition cavity (7), the piston bodies (9) are arranged in parallel to the axial direction of a steering engine, each piston body (9) is communicated with the compressed air transition cavity (7) through a pneumatic conversion device (4), the acting end of each piston body (9) is connected with a rudder wing transmission mechanism (3), the rudder wing transmission mechanism (3) is connected with a corresponding rudder wing (2), the driver (1) is arranged at the tail part of the steering engine, the driver (1) is electrically connected with the pneumatic conversion device (4), and the pneumatic conversion device (4) is controlled by the driver (1) to release the high-pressure gas in the compressed air transition cavity (7) to the cylinder body (9) in which the piston body (9) is located And the piston body (9) pushes the rudder wing transmission mechanism (3) to move so as to drive the rudder wing (2) to rotate around the locking pin, so that the posture and the flight direction of the missile are changed.
2. The 40 mm pneumatic steering engine system with an air source according to claim 1, wherein the pneumatic switching device (4) is an electromagnetic valve, and the response time of the dynamic characteristic of the electromagnetic valve is less than or equal to 6 milliseconds.
3. The 40-millimeter pneumatic steering engine system with an air source according to claim 1, wherein the high-pressure gas in the combined high-pressure gas cylinder (6) is nitrogen, and the nitrogen in the combined high-pressure gas cylinder (6) can work for more than 20 seconds in a cylinder body where the piston body (9) is located.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210167500.9A CN114543600A (en) | 2022-02-23 | 2022-02-23 | 40 mm pneumatic steering engine system with air source |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210167500.9A CN114543600A (en) | 2022-02-23 | 2022-02-23 | 40 mm pneumatic steering engine system with air source |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114543600A true CN114543600A (en) | 2022-05-27 |
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ID=81677742
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210167500.9A Pending CN114543600A (en) | 2022-02-23 | 2022-02-23 | 40 mm pneumatic steering engine system with air source |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114543600A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115096146A (en) * | 2022-07-18 | 2022-09-23 | 南京理工大学 | Control surface deflection and active sealing locking mechanism suitable for PGK wing bucket structure |
| CN115962685A (en) * | 2022-12-29 | 2023-04-14 | 北京自动化控制设备研究所 | Folding control surface locking and unfolding mechanism and guided projectile with same |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115096146A (en) * | 2022-07-18 | 2022-09-23 | 南京理工大学 | Control surface deflection and active sealing locking mechanism suitable for PGK wing bucket structure |
| CN115096146B (en) * | 2022-07-18 | 2023-07-18 | 南京理工大学 | Control surface deflection and active sealing locking mechanism suitable for PGK wing barrel structure |
| CN115962685A (en) * | 2022-12-29 | 2023-04-14 | 北京自动化控制设备研究所 | Folding control surface locking and unfolding mechanism and guided projectile with same |
| CN115962685B (en) * | 2022-12-29 | 2024-09-06 | 北京自动化控制设备研究所 | Folding control surface locking and unfolding mechanism and guided projectile with same |
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