CN218566316U - Miniature missile - Google Patents
Miniature missile Download PDFInfo
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- CN218566316U CN218566316U CN202222306986.8U CN202222306986U CN218566316U CN 218566316 U CN218566316 U CN 218566316U CN 202222306986 U CN202222306986 U CN 202222306986U CN 218566316 U CN218566316 U CN 218566316U
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- 230000037431 insertion Effects 0.000 claims description 2
- 238000013461 design Methods 0.000 abstract description 5
- 238000000034 method Methods 0.000 description 4
- 238000012986 modification Methods 0.000 description 4
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- 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
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- 239000007787 solid Substances 0.000 description 1
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Abstract
The application discloses a micro missile which comprises a missile body consisting of a guide head cabin, a thermal battery cabin, a rudder cabin, a missile control cabin, a guidance control cabin, an engine cabin and a tail wing section, wherein the missile body is in modular design and is sequentially assembled from a warhead to a missile tail; the rudder cabin comprises four foldable rudder pieces which are arranged in an axisymmetric cross shape, the tail section comprises a roll-arc wing unit, the roll-arc wing unit comprises four roll-arc wing blades which are arranged in an axisymmetric cross shape, and one roll-arc wing blade is configured to be consistent in the root part of the roll-arc wing blade with the orientation of one foldable rudder piece after being unfolded. The micro missile provided by the application has better structural characteristics and aerodynamic characteristics.
Description
Technical Field
The application relates to the structural design of an accurate guided weapon, in particular to the structural design of a micro guided missile.
Background
With the rapid development of the small unmanned aerial vehicle, the micro missile adaptive to the small unmanned aerial vehicle can be changed into good hands. Several micro missiles have been developed at home and abroad, and can be hung on a small unmanned aerial vehicle and also can be matched with a launching system to launch individual soldiers. The micro missile has high practical value for striking a specific target at a high value and a short distance, so that a multi-purpose and multi-platform launching micro missile with a reasonable structure and high integration needs to be researched.
QN202 is the miniature guided missile of independent research and development in our country, is a lightweight, accurate modern weapon, and this guided missile is fit for single hand-carry when fighting, because the guided missile is about 40 centimetres long, and 4 centimetres wide, guided missile is only a kilogram heavy, and the rifle type launcher of guided missile is 3.5 kilograms heavily. Each soldier can carry the launcher and the missile with six QN202 missiles by one military backpack-type storage box, and the pocket is also called the smallest missile in the world. The functional requirements of the micro missile are consistent with those of a common missile, but the micro missile has high requirements on the layout of electrical equipment, cable routing and structural layout in the missile because of the small size of the micro missile.
Therefore, for the micro missile, a highly integrated system design is required, and through the high integration of the electrical equipment, the space and the weight occupied by the electrical equipment are reduced, and the use of a cable on the missile can also be reduced.
Disclosure of Invention
The application aims to design a highly integrated micro missile according to the functional requirements of the micro missile.
To this end, some embodiments of the present application provide a micro missile comprising a projectile body consisting of a nose module, a thermal battery compartment, a rudder compartment, a war-guiding compartment, a guidance control compartment, an engine compartment and a tail section, which are modularly designed and assembled in sequence from the warhead to the tail; the rudder cabin comprises four foldable rudder pieces which are arranged in an axisymmetric cross shape, the tail wing section comprises a rolling arc wing unit, the rolling arc wing unit comprises four rolling arc wing blades which are arranged in an axisymmetric cross shape, a tail circuit board is arranged at the tail part of the tail wing section, and a falling plug is arranged on the tail circuit board.
In some embodiments, an ignition pulse signal is fed directly to an ignition head of the engine compartment through the breakaway plug.
In some embodiments, one of said rolling arc wing blades is configured such that its root is oriented in line with one of said foldable rudder blades after deployment.
In some embodiments, the foldable rudder blade is configured such that prior to launch, the foldable rudder blade is in a stowed position within the rudder nacelle, the cambered wing blades are circumferentially folded against the outer contour of the tail wing section; the foldable rudder blade is axially unfolded and axially angled to the rudder nacelle after launch, and the roll-arc wing blades are circumferentially unfolded and circumferentially angled to the tail section.
In some embodiments, the rolling arc wing unit comprises a rolling arc wing front frame, a rolling arc wing rear frame, and four rolling arc wing blades pre-pressed between the rolling arc wing front frame and the rolling arc wing rear frame by torsion springs; each rolling arc wing blade is circumferentially matched with a rolling arc wing rear frame through a shaft of the rolling arc wing blade and the torsion spring matched on the shaft, and the torsion spring is configured to drive the rolling arc wing blade to be circumferentially unfolded around the shaft of the rolling arc wing blade after the micro missile is launched; each of the roll arc wing blades is also axially engaged with the roll arc wing nose piece by the shaft and a compression spring engaged on the shaft, the compression spring configured to axially urge the roll arc wing blade to a positioning position consistent with the foldable rudder piece orientation after the roll arc wing blade is deployed.
In some embodiments, the foldable rudder blade has a rearwardly unfolded configuration or a forwardly unfolded configuration.
In some embodiments, the foldable rudder sheet is a low aspect ratio rudder sheet and the rollable cambered wing blade is a high aspect ratio rollable cambered wing blade.
In some embodiments, the electrical system of the micro missile is arranged in the guidance head cabin, the thermal battery cabin, the rudder cabin, the guidance control cabin and the tail circuit board of the tail wing section, and the connecting wires of the electrical equipment of the whole missile are distributed in the bulkhead wiring grooves of each cabin section.
In some embodiments, the guidance control bay includes a guidance control device, a MEMS inertial measurement unit, and a bay structure.
In some embodiments, the drop plug is a micro rectangular connector, and missile drop separation is performed in a tangential manner; or a double row of jacks.
The miniature missile according to some embodiments of the present application is, in order from the warhead to the missile tail, a leader cabin, a thermal battery cabin, a rudder cabin, a missile cabin, a guidance control cabin, an engine cabin and a shedding plug, and the whole missile is modularly assembled through the above cabin sections. Simple structure, the cabin section replacement is convenient. The provided micro guided missile adopts the pneumatic layout of rudder pieces and tail vanes with front and back cross structures, and is suitable for the high-efficiency operation of the micro guided missile.
Some embodiments of the application provide a micro missile with a specific tail section structure, wherein a tail circuit board is arranged at the tail part and a drop plug is connected to the circuit board, which is beneficial to sharing part of electrical equipment of the micro missile, so that the distribution of the electrical equipment is more reasonable.
The rocket engine in the embodiment can adopt an external fire control ignition mode, directly sends an ignition pulse signal to the ignition head through the falling plug, does not use a guidance control device to generate the ignition pulse signal, and achieves the function of simplifying the guidance control device as much as possible.
This summary is not intended to identify key or essential features of the claimed subject matter, nor is it intended to be used alone to determine the scope of the claimed subject matter. The subject matter should be understood by reference to appropriate portions of the entire specification of the disclosure, any or all of the drawings, and each claim.
The foregoing and other features and examples will be described in more detail in the following specification, claims and drawings.
The terms and expressions which have been employed are used as terms of description and not of limitation, and there is no intention in the use of such terms and expressions of excluding any equivalents of the features shown and described or portions thereof. Nevertheless, it will be understood that various modifications may be made within the scope of the claimed system and method. Thus, while the present systems and methods have been specifically disclosed by way of examples and optional features, those skilled in the art will recognize modifications and variations of the concepts disclosed herein, and such modifications and variations are considered to be within the scope of the systems and methods as defined by the following claims.
Drawings
FIG. 1 is an elevation view of a micro-missile according to an embodiment of the present application;
FIG. 2 is a rear view of a micro-missile according to an embodiment of the present application;
FIG. 3 is a cross-sectional view of a micro-missile according to an embodiment of the present application;
FIG. 4 is a front view of a roll wing unit of a micro missile according to an embodiment of the application.
Detailed Description
In the following description, various examples of micro missiles are described. For purposes of explanation, specific configurations and details are set forth in order to provide a thorough understanding of the embodiments. It will be apparent, however, to one skilled in the art that certain embodiments may be practiced or carried out without each of the disclosed details. Furthermore, well-known features may be omitted or simplified to help prevent any confusion over the novel features described herein.
The following high-level summary is intended to provide a basic understanding of some novel innovations depicted in the accompanying drawings and presented in the corresponding description provided below.
Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
Referring to fig. 1, a micro missile according to an embodiment of the present application is composed of a leader bay 10, a thermal battery bay 20, a rudder bay 30, a guidance bay 40, a guidance control bay 50, an engine bay 60, and a tail panel 70, which are modularly designed and assembled in order from a warhead to a wartail; and one or more of connection modes of hole shaft positioning, positioning pin limiting and screw fixing are adopted between each cabin and each section so as to ensure fixed connection. The overall pneumatic scheme of the micro missile adopts a ten-plus-ten duck type layout. By adopting the modular structure scheme, the replacement and expansion of each module can be realized.
In this application, unless otherwise defined, the warhead, head, front, and front all refer to the orientation of the direction of travel of the projectile after launch, and the wartail, tail, back, and back all refer to the orientation of the projectile after launch, opposite the direction of travel. The axial direction refers to the direction of the long axis of the missile body of the missile and also becomes the front-back direction and the head-tail direction. Circumferential refers to the direction along the outer circumference of the cross-section of the projectile.
The guide head cabin 10 can realize modular reloading, and a guide head 11 is installed in the guide head cabin 10. The seeker 11 can be a laser seeker, an infrared seeker or a visible light seeker, the laser seeker is more suitable for unmanned aerial vehicle platform emission, and the unmanned aerial vehicle can carry out local irradiation local emission. The infrared guide head and the visible light guide head are mostly used for individual soldier emission.
The thermal battery compartment 20 is arranged with a thermal battery 21, eight cabling channels are designed in the thermal battery compartment housing wall, the wires leading to the head compartment 10 and the thermal battery 21 can be arranged extending from the side wall to the engine compartment and tail section 70 of the missile tail, wherein the thermal battery 21 is activated before the missile is launched and supplies power to the electrical devices of the whole missile after the missile is launched.
The rudder cabin 30 of the micro missile is designed according to the form of a rudder cabin section, the diameter of the rudder cabin section 30 is consistent with that of the missile body, and the rudder 31 is a four-blade rudder and comprises four rudder pieces 311. The four rudders 311 are of a foldable construction, i.e. from an extended position at an angle to the axis of the projectile, as shown in fig. 1, folded axially along the long axis of the projectile to a stowed position parallel to the axis of the projectile. In this embodiment, the configuration may be optimized such that four rudder pieces are retracted into the rudder cabin body, so that the rudder cabin body maintains a smooth arc line, the missile is in the storage box and the launch canister, the rudder pieces are all folded inside the cabin body, after the launch canister is launched, the four rudder pieces control the rudder pieces to perform axial unfolding action, after the rudder pieces are unfolded out of the canister, the rudder pieces are unfolded forward to form an angle with the axis of the missile body, and the rudder cabin 30 is connected with the thermal battery cabin 20 and the war inducing cabin 40 respectively in a pre-buried line manner.
The fuse control cabin 40 comprises an electronic fuse, a warhead and a cabin structure, and the electronic fuse is electrically connected with a guidance control device 51 in the guidance control cabin 50 backwards through an on-missile cable of the cabin wall of the cabin structure for power supply and communication.
The micro missile is highly integrated with missile-borne electrical equipment, a guidance control cabin 50 is provided with a guidance control device 51 and partial missile-borne cables, the guidance control device 51 comprises a control unit part, an MEMS (micro electro mechanical systems) inertia measurement unit and a structure, the control unit part carries out navigation and flight control calculation by collecting data of the MEMS inertia measurement unit and a seeker, and meanwhile, flight time sequence control is carried out according to the working flow of the missile, such as battery activation, fuze power supply, fuze solution and the like.
The engine compartment 60 contains a solid rocket engine, an ignition head 61 and an engine housing, wherein the ignition head 61 may be located at the front of the engine compartment 60 as shown in fig. 3, or may be located at the rear of the engine compartment 60 in other embodiments; the rocket engine in the embodiment can adopt an external fire control ignition mode, directly sends an ignition pulse signal to the ignition head 61 through the falling plug through a cable, does not use a guidance control device to generate an ignition signal, and achieves the function of simplifying the guidance control device 51 as much as possible.
The tail wing section 70 comprises a rolling arc wing unit 71, and each blade of the rolling arc wing unit 71 forms an angle with the projectile body after being unfolded, and the function of the rolling arc wing unit 71 is mainly to provide the lift force and the required stabilizing moment of trim flight; in this embodiment, the micro missile 100 has four rolling arc wing blades, and the rolling arc wing blades are fixed after being unfolded, and form a 'ten' + 'ten' layout together with the duck rudder after being unfolded. Each of the rolling arc wing units 71 is composed of a rolling arc wing front frame 711, a rolling arc wing rear frame 712, a rolling arc wing blade 713, four compression springs 714, and four torsion springs 715. The root of each rolling arc wing blade 713 is provided with a shaft 7131, two ends of the shaft 7131 are inserted into a compression spring 714 of a rolling arc wing front frame 711 and a torsion spring 715 of a rolling arc wing rear frame 712, and the rolling arc wing blades 713 are allowed to freely rotate around the shaft 7131 within a certain range. Each curling wing blade 713 is biased circumferentially by a torsion spring 715 into compliance with the outer profile of the tail section 70 and is biased axially aft of the projectile by a compression spring 714. After the missile is launched out of the barrel, the blades 713 of the curling arc wings are pushed by the torsion spring 715 to be flicked, and are circumferentially unfolded around the shaft 7131 relative to the outline of the missile body to reach the position of the positioning groove, and then are pressed into the positioning groove through the compression spring 714 to be fixed in place, as shown in fig. 4, the positioning groove is arranged at the position where the blades of the curling arc wings are aligned with the rudder piece. For example, such that the axis of each of the detents coincides with the axis of the foldable rudder. As described above, the rear roll-arc wing frame 712 is provided with four positioning slots for positioning the roll-arc wing blades 713, so that the orientation of the roll-arc wing blades 713 is consistent with the orientation of the foldable rudder sheet of the four-blade steering engine on the front side of the missile, for example, as shown in fig. 2, the positioning slots are arranged at positions where the part of each roll-arc wing blade 713 near the shaft 7131 is consistent with the orientation of the foldable rudder sheet 311 of the corresponding steering engine.
A circular tail circuit board 72 with a hollow middle is arranged around the engine tail nozzle, double rows of holes are arranged on the tail circuit board 72 to serve as falling-off plugs 73, and 16 point number circuit boards are fixed on an engine shell through four axial screws. Because the size of the micro missile is small, double rows of row holes are selected as the falling plug 73, and after the engine is ignited, the falling plug 73 is disconnected with the row pins which are oppositely inserted by the fire control system.
Due to the tension of the micro missile structure, routing channels need to be arranged as much as possible when the cabin section structure is designed, for example, the routing channels are reserved in the inner walls of the shells of all the cabin sections.
As an alternative to the above embodiment: the micro guided missile can adopt a micro rectangular connector as a falling plug 73, and guided missile falling and insertion separation is carried out in a tangent mode;
as an alternative to the above embodiment: the micro missile can adopt a configuration that a folding rudder is unfolded backwards to replace the configuration that the folding rudder is unfolded forwards in the embodiment;
as an alternative to the above embodiment: the micro missile can select a rotatable folding arc wing rolling unit to replace the existing arc wing rolling unit;
fixed connection in this application can adopt one or more in the connected mode of hole axle location, locating pin spacing, screw fixation in order to guarantee fixed connection.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Moreover, while advantages associated with certain embodiments of the technology have been described in the context of those embodiments, other embodiments may also exhibit such advantages, and not all embodiments need necessarily exhibit such advantages to fall within the scope of the technology. Accordingly, the present disclosure and associated techniques may include other embodiments not explicitly shown or described herein. Accordingly, the disclosure is to be limited only by the following claims.
Reference numerals:
guide head cabin 10
Guide head 11
Thermal battery 21
Steering engine 31
War-leading cabin 40
Roll arc wing unit 71
Roll arc wing rear frame 712
The plug 73 is disengaged.
Claims (10)
1. A micro missile, which is characterized in that: the missile comprises a missile body consisting of a guidance head cabin, a thermal battery cabin, a rudder cabin, a missile cabin, a guidance control cabin, an engine cabin and an empennage section which are designed in a modularized manner and assembled in sequence from a missile head to a missile tail; the rudder cabin comprises four foldable rudder pieces which are arranged in an axisymmetric cross shape, the tail wing section comprises a rolling arc wing unit, the rolling arc wing unit comprises four rolling arc wing blades which are arranged in an axisymmetric cross shape, a tail circuit board is arranged at the tail part of the tail wing section, and a falling plug is arranged on the tail circuit board.
2. A micro-missile according to claim 1, wherein: and directly sending an ignition pulse signal to an ignition head of the engine compartment through the shedding plug.
3. A micro-missile according to claim 1, wherein: the foldable rudder sheet is configured to be in a stowed position within the rudder nacelle prior to launch, the cambered wing blades being circumferentially folded against the outer profile of the tail wing section; the foldable rudder blade is axially unfolded and axially angled to the rudder nacelle after launch, and the roll-arc wing blades are circumferentially unfolded and circumferentially angled to the tail section.
4. A micro-missile according to claim 3, wherein: the rolling arc wing unit comprises a rolling arc wing front frame, a rolling arc wing rear frame and four rolling arc wing blades pre-pressed between the rolling arc wing front frame and the rolling arc wing rear frame through torsion springs; each rolling arc wing blade is circumferentially matched with the rolling arc wing rear frame through a shaft of the rolling arc wing blade and the torsion spring matched on the shaft, and the torsion spring is configured to drive the rolling arc wing blade to circumferentially expand around the shaft of the rolling arc wing blade after the micro missile is launched; each of the roll arc wing blades is also axially engaged with the roll arc wing nose piece by the shaft and a compression spring engaged on the shaft, the compression spring configured to axially urge the roll arc wing blade to a positioning position consistent with the foldable rudder piece orientation after the roll arc wing blade is deployed.
5. A micro-missile according to claim 3, wherein: the foldable rudder sheet has a backward unfolded configuration or a forward unfolded configuration.
6. A micro-missile according to claim 1, wherein: the foldable rudder sheet is a rudder sheet with a small aspect ratio, and the rolling arc wing blade is a rolling arc wing blade with a large aspect ratio.
7. A micro-missile according to claim 1, wherein: the electric system of the micro missile is arranged in the guide head cabin, the thermal battery cabin, the rudder cabin, the missile control cabin, the guidance control cabin and the tail circuit board of the tail wing section, and connecting wires of the whole missile electric equipment are distributed in bulkhead wiring grooves of all cabin sections.
8. A micro-missile according to claim 1, wherein: the guidance control cabin comprises a guidance control device, an MEMS inertia measurement unit and a cabin section structure.
9. A micro-missile according to claim 1, wherein: wherein one of said rolling arc wing blades is configured such that its root is oriented in line with one of said foldable rudder blades after deployment.
10. A micro-missile according to claim 1, wherein: the shedding plug is a micro rectangular connector, guided missile shedding and insertion separation is carried out in a tangent mode, or double-row jacks are formed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222306986.8U CN218566316U (en) | 2022-08-30 | 2022-08-30 | Miniature missile |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222306986.8U CN218566316U (en) | 2022-08-30 | 2022-08-30 | Miniature missile |
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| Publication Number | Publication Date |
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| CN218566316U true CN218566316U (en) | 2023-03-03 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202222306986.8U Active CN218566316U (en) | 2022-08-30 | 2022-08-30 | Miniature missile |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2814624C1 (en) * | 2023-08-29 | 2024-03-01 | Акционерное общество "Научно-производственное объединение "СПЛАВ" им. А.Н. Ганичева" | Missile stabilizer |
| CN117944869A (en) * | 2024-03-27 | 2024-04-30 | 山西观复智能科技有限公司 | Semi-flexible three-blade hub |
-
2022
- 2022-08-30 CN CN202222306986.8U patent/CN218566316U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2814624C1 (en) * | 2023-08-29 | 2024-03-01 | Акционерное общество "Научно-производственное объединение "СПЛАВ" им. А.Н. Ганичева" | Missile stabilizer |
| RU2814640C1 (en) * | 2023-09-04 | 2024-03-04 | Акционерное общество "Научно-производственное объединение "СПЛАВ" имени А.Н. Ганичева" | Missile |
| CN117944869A (en) * | 2024-03-27 | 2024-04-30 | 山西观复智能科技有限公司 | Semi-flexible three-blade hub |
| CN117944869B (en) * | 2024-03-27 | 2024-05-31 | 山西观复智能科技有限公司 | Semi-flexible three-blade hub |
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Effective date of registration: 20231128 Address after: Room 705, 7th Floor, Shangyuan Huizhan Science and Technology Park, Intersection of Huisheng Road and Yanglin Road, High tech Zone, Hefei City, Anhui Province, 230000 Patentee after: Zhongke Huakong Aerospace Technology Hefei Co.,Ltd. Address before: 101299 39-14, Floor 3, No. 39, Pinggu South Street, Pinggu Town, Pinggu District, Beijing Patentee before: Huake Intelligent Control (Beijing) Technology Co.,Ltd. |