CN109579637B - Missile attitude control mechanism without control surface - Google Patents
Missile attitude control mechanism without control surface Download PDFInfo
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- CN109579637B CN109579637B CN201811495836.8A CN201811495836A CN109579637B CN 109579637 B CN109579637 B CN 109579637B CN 201811495836 A CN201811495836 A CN 201811495836A CN 109579637 B CN109579637 B CN 109579637B
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- Prior art keywords
- missile body
- drainage
- missile
- tail end
- drainage tube
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- 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
-
- 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
Abstract
The utility model provides a no control surface guided missile attitude control mechanism, includes the guided missile body, has seted up a plurality of drainage holes on each side of its bullet body of guided missile body, and each drainage hole corresponds a drainage tube of UNICOM respectively, and each drainage tube extends until the tail end bottom surface of guided missile body in the bullet body, all is provided with the governing valve on each drainage tube, controls each drainage tube internal flow through the governing valve. According to the missile attitude adjusting device, a steering engine is not needed, the characteristics of the process are utilized, the side surface of the missile body is communicated with the bottom surface of the tail end through the drainage tube, namely, the low-pressure area of the bottom is communicated with the high-pressure area of the missile body, and the control force for adjusting the attitude of the missile is formed. Meanwhile, the flight resistance of the missile is reduced to a certain extent due to the rise of the pressure of the bottom surface of the tail end.
Description
Technical Field
The invention relates to the technical field of missile attitude control, in particular to an attitude control mechanism designed for a missile without a control surface.
Background
Missiles are a significant weapon equipment, and their development is receiving attention from various countries in the world. In order to realize the attitude adjustment of the missile in the flight process, the tail of the traditional missile is provided with two, four or more control surfaces. When the posture of the missile needs to be adjusted, the angle between the control surface of the tail of the missile and the incoming flow is reasonably adjusted, so that corresponding control force is generated on the control surface. The control force acts on the gravity center of the missile to form a corresponding control moment, so that the posture of the missile is adjusted.
The control mode of adjusting the missile attitude is realized through the control surface, the control method has very intuitive and obvious control effect, and is widely applied to various aircrafts. A complete aircraft attitude control law can be obtained through the wind tunnel experiment and simulation in the early stage and is used for guiding the attitude control in the actual flight process. However, this control method also has certain problems:
(1) The control surface generates control force, and meanwhile, the control surface and the incoming air flow have a certain attack angle, so that the overall resistance of the aircraft is increased to a certain degree.
(2) The adjustment of the control surfaces requires steering engines to control, which necessitates that the aircraft carries additional structural weight. For a hypersonic aircraft, the steering engine is required to be larger to keep the state of a control surface, so that the effective load of the aircraft is reduced.
(3) The control surface of the tail part brings certain difficulties to the storage and transportation of the aircraft.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a control surface-free missile attitude control mechanism.
In order to realize the technical purpose of the invention, the following technical scheme is adopted:
the missile attitude control mechanism without the control surface comprises a missile body and is characterized in that a plurality of drainage holes are formed in each side surface of a missile body of the missile body, each drainage hole corresponds to one drainage tube in communication, and each drainage tube extends in the missile body until reaching the bottom surface of the tail end of the missile body. Furthermore, each drainage tube is provided with an adjusting valve. For the missile, the air inflow separates at the tail end of the missile body to form a low-pressure area, so that a large pressure difference is formed between the front and the rear of the missile, which is also an important part of the missile resistance. All side surfaces of the missile body are connected with the bottom surface of the tail end through the drainage holes and the drainage tubes, and high-pressure air flow at the missile body can enter the bottom surface of the tail end through the drainage holes and the drainage tubes, so that the pressure at the bottom end of the missile is improved, and the resistance of the missile is reduced to a certain extent. Meanwhile, in order to realize the adjustable posture of the missile, the mode of arranging the regulating valves in the drainage tubes is adopted. The opening and closing of each drainage hole are controlled by controlling the opening and closing of the regulating valve on each drainage pipe; the flow in each drainage tube is controlled by adjusting each regulating valve, so that the pressure distribution of the bottom surface of the tail end of the missile body is influenced. Through reasonable combination of the regulating valves, the posture of the missile can be controlled.
The missile body is a special-shaped missile, and can also be a vertically symmetrical or horizontally symmetrical missile. Namely the missile body and the bottom surface of the tail end of the missile body are irregularly-shaped missiles, or the missile body and the bottom surface of the tail end of the missile body are vertically or horizontally symmetrical missiles. No matter what type of missile body is, as long as the missile body is provided with a missile body and a tail end bottom surface, the method can be adopted, and the purposes of reducing the resistance of the missile and controlling the attitude of the missile are realized by arranging the drainage holes and the drainage tubes.
Taking the missile body as an axisymmetric structure as an example, a plurality of pairs of axisymmetric drainage holes are formed on each symmetrical side surface of the missile body. Drainage tubes communicated with each pair of axisymmetric drainage holes and drainage tube outlets are respectively distributed in the missile body and on the bottom surface of the tail end of the missile body in an axisymmetric manner.
In the invention: on the body of the missile that is close to its tail end of missile body, two drainage holes have been seted up to the downside symmetry, the drainage tube of two drainage holes UNICOM separately also is upper and lower symmetric distribution in the body of the missile, wherein the upside at the tail end bottom surface of missile body is established to the drainage tube export that drainage hole corresponds on the body side of the missile, the drainage tube export that drainage hole corresponds on the body downside of the missile body is established at the downside of the tail end bottom surface of missile body, and two drainage tube exports are upper and lower symmetric distribution on the tail end bottom surface of missile body. If the low head of missile body is realized, the regulating valve corresponding to the drainage hole on the upper side surface is opened, and the regulating valves corresponding to the drainage holes on other side surfaces, namely the lower side surface, the left side surface and the right side surface, are completely closed. The pressure of (2) is increased; because the regulating valve corresponding to the drainage hole on the lower side surface is closed, the low-pressure area is formed near the outlet of the drainage tube on the lower side surface, and the high pressure is applied to the upper part of the bottom surface of the tail end of the missile body, the missile body generates downward head lowering moment, and the posture control of the head lowering of the missile body is realized; if the head of the missile body needs to be lifted, the regulating valve corresponding to the drainage hole in the lower side surface is opened, and the regulating valve corresponding to the drainage hole in the upper side surface, the left side surface and the right side surface is closed.
In the invention: two drainage holes are symmetrically formed in the left side surface and the right side surface of the missile body close to the tail end of the missile body, drainage tubes communicated with the drainage holes are symmetrically distributed in the missile body, drainage tube outlets corresponding to the drainage holes in the left side surface of the missile body are formed in the left side of the bottom surface of the tail end of the missile body, drainage tube outlets corresponding to the drainage holes in the right side surface of the missile body are formed in the right side of the bottom surface of the tail end of the missile body, and the two drainage tube outlets are symmetrically distributed in the left side and the right side of the bottom surface of the tail end of the missile body. If the left side that will realize the guided missile body is inclined to one side, open the governing valve that drainage hole corresponds on the right flank, and other each side is the governing valve that drainage hole corresponds on the side of going up, downside and the left surface is all closed. At this time, the high-pressure air flow flows out from the draft tube on the right side surface, and the pressure near the outlet of the draft tube on the right side surface is increased; because the regulating valve corresponding to the drainage hole on the left side surface is closed, the position near the outlet of the drainage pipe on the left side surface is a low-pressure area, and the right side of the bottom surface of the tail end of the missile body is subjected to high pressure, the missile body generates left-biased moment, and the posture control of the left-biased missile body is realized; if the right deviation of the missile body is required to be realized, the regulating valve corresponding to the drainage hole in the left side surface is opened, and the regulating valve corresponding to the drainage hole in the right side surface is closed.
In the invention, the regulating valve is an electronic regulating valve which is electrically controlled, and the flow of each drainage tube is regulated through the electronic regulating valve to control the posture change speed of the missile body.
Compared with the prior art, the invention can produce the following technical effects:
(1) The invention cancels the structure of the tail rudder of the original missile, changes the structure into the form of a drainage tube, and the designed drainage tube connects the missile body side surface with the bottom surface of the missile tail end to form the control force for adjusting the posture of the missile body. The invention does not need additional steering engine, thus greatly reducing the weight of the structure.
(2) The invention fully utilizes the characteristics of the flow field, can realize the adjustment of the posture of the missile body through the drainage tube, the switch of the drainage tube and the regulating valve for controlling the flow inside the drainage tube, simultaneously improves the pressure at the bottom end of the missile, and reduces the resistance of the missile to a certain extent.
(3) The invention has no control surface, and is convenient for transportation, storage and loading.
Drawings
FIG. 1 is a schematic view of the structure of the present invention;
FIG. 2 is a schematic diagram of the distribution of the internal drainage tubes of the projectile body in accordance with one embodiment of the present invention;
in the figure:
1. a missile body; 2. a drainage hole; 3. a drainage tube; 4. and adjusting the valve.
Detailed Description
Embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.
Referring to fig. 1, the invention provides a control surface-free missile body attitude control mechanism which comprises a missile body 1, wherein a plurality of drainage holes 2 are formed in each side surface of a missile body of the missile body 1, each drainage hole 2 is respectively communicated with a drainage tube 3 correspondingly, each drainage tube 3 extends in the missile body until reaching the bottom surface of the tail end of the missile body 1, each drainage tube 2 is provided with an adjusting valve 4, and the flow rate in each drainage tube 2 is controlled through the adjusting valve 4. The regulating valve is an electronic regulating valve which is electrically controlled, the flow of each drainage tube is regulated through the electronic regulating valve, and the speed of the posture change of the missile body is controlled.
Referring to fig. 1 and 2, the missile body 1 is of an axisymmetric structure. A plurality of pairs of axially symmetric drainage holes 2 are arranged on each symmetrical side surface of the missile body 1. Drainage tubes 3 communicated with each pair of axisymmetric drainage holes 2, and drainage tube outlets are respectively distributed in the missile body and on the bottom surface of the tail end of the missile body in an axisymmetric manner.
Two drainage holes are symmetrically formed in the upper side surface and the lower side surface of the missile body close to the tail end of the missile body, drainage tubes communicated with the drainage holes are also symmetrically distributed in the missile body from top to bottom, drainage tube outlets corresponding to the drainage holes in the upper side surface of the missile body are formed in the upper side of the bottom surface of the tail end of the missile body, drainage tube outlets corresponding to the drainage holes in the lower side surface of the missile body are formed in the lower side of the bottom surface of the tail end of the missile body, and the two drainage tube outlets are symmetrically distributed in the upper side and the lower side of the bottom surface of the tail end of the missile body.
Meanwhile, two drainage holes are symmetrically formed in the left side surface and the right side surface of the missile body close to the tail end of the missile body, drainage tubes communicated with the two drainage holes are symmetrically distributed in the missile body, drainage tube outlets corresponding to the drainage holes in the left side surface of the missile body are formed in the left side of the bottom surface of the tail end of the missile body, drainage tube outlets corresponding to the drainage holes in the right side surface of the missile body are formed in the right side of the bottom surface of the tail end of the missile body, and the two drainage tube outlets are symmetrically distributed in the left side and the right side of the bottom surface of the tail end of the missile body.
If the head of the missile body is to be lowered, the regulating valve corresponding to the drainage hole in the upper side surface is opened, and the regulating valves corresponding to the drainage holes in other side surfaces, namely the lower side surface, the left side surface and the right side surface, are completely closed. The pressure of (2) is increased; because the regulating valve corresponding to the drainage hole on the lower side surface is closed, the low-pressure area is formed near the outlet of the drainage tube on the lower side surface, and the high pressure is applied to the upper part of the bottom surface of the tail end of the missile body, the missile body generates downward head lowering moment, and the posture control of the head lowering of the missile body is realized; if the head of the missile body needs to be lifted, the regulating valve corresponding to the drainage hole in the lower side surface is opened, and the regulating valve corresponding to the drainage hole in the upper side surface, the left side surface and the right side surface is closed.
If the left side that will realize the guided missile body is inclined to one side, open the governing valve that drainage hole corresponds on the right flank, and other each side is the governing valve that drainage hole corresponds on the side of going up, downside and the left surface is all closed. At this time, the high-pressure air flow flows out from the draft tube on the right side surface, and the pressure near the outlet of the draft tube on the right side surface is increased; because the regulating valve corresponding to the drainage hole on the left side surface is closed, the low-pressure area is arranged near the outlet of the drainage tube on the left side surface, and the right side of the bottom surface of the tail end of the missile body is subjected to high pressure, the missile body generates a leftward left deviation moment, and the attitude control of the missile body is realized; if the missile body needs to be rightwards deviated, the adjusting valve corresponding to the drainage hole in the left side surface is opened, and the adjusting valve corresponding to the drainage hole in the right side surface is closed.
The embodiment of the invention is not limited to the above-mentioned examples, and the cross-sectional shape, size, number and distribution of the drainage holes on the bullet body are not limited. Through the reasonable combination of the regulating valves, the regulating valves corresponding to the corresponding drainage holes are opened or closed, or the corresponding regulating valves are regulated to control the flow in the corresponding drainage tubes, so that the pressure distribution condition on the ground at the tail end of the missile body can be changed, and the accurate control on the posture of the missile is realized.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (1)
1. The utility model provides a no control surface guided missile attitude control mechanism, includes the guided missile body, its characterized in that: a plurality of drainage holes are formed in each side surface of the missile body, each drainage hole is correspondingly communicated with a drainage tube, and each drainage tube extends in the missile body until reaching the bottom surface of the tail end of the missile body; the missile body is of an axisymmetric structure; the upper side and the lower side of the missile body close to the tail end of the missile body are symmetrically provided with two drainage holes, drainage tubes communicated with the drainage holes respectively are also symmetrically distributed in the missile body up and down, drainage tube outlets corresponding to the drainage holes in the upper side surface of the missile body are arranged on the upper side of the bottom surface of the tail end of the missile body, drainage tube outlets corresponding to the drainage holes in the lower side surface of the missile body are arranged on the lower side of the bottom surface of the tail end of the missile body, and the two drainage tube outlets are symmetrically distributed in the up and down direction on the bottom surface of the tail end of the missile body; two drainage holes are symmetrically formed in the left side surface and the right side surface of the missile body close to the tail end of the missile body, drainage tubes communicated with the two drainage holes are symmetrically distributed in the missile body in a left-right mode, drainage tube outlets corresponding to the drainage holes in the left side surface of the missile body are formed in the left side of the bottom surface of the tail end of the missile body, drainage tube outlets corresponding to the drainage holes in the right side surface of the missile body are formed in the right side of the bottom surface of the tail end of the missile body, and the two drainage tube outlets are symmetrically distributed in the left-right mode on the bottom surface of the tail end of the missile body;
each drainage tube is provided with an adjusting valve; all side surfaces of the missile body are connected with the bottom surface of the tail end through the drainage holes and the drainage tubes, high-pressure air flow at the missile body enters the bottom surface of the tail end through the drainage holes and the drainage tubes, so that the pressure at the bottom end of the missile is improved, the resistance of the missile is reduced, meanwhile, the opening and closing of the drainage holes are controlled by controlling the switches of the regulating valves on the drainage tubes, and the flow in the drainage tubes is controlled by regulating the regulating valves, so that the pressure distribution of the bottom surface of the tail end of the missile body is influenced, and the posture of the missile is controlled;
if the missile body is lowered, the regulating valves corresponding to the drainage holes on the upper side surface are opened, and the regulating valves corresponding to the drainage holes on the lower side surface, the left side surface and the right side surface are all closed, at the moment, high-pressure air flows out of the drainage tube on the upper side surface, and the pressure near the outlet of the drainage tube on the upper side surface is increased; because the regulating valve corresponding to the drainage hole on the lower side surface is closed, the low-pressure area is formed near the outlet of the drainage tube on the lower side surface, and the high pressure is applied to the upper part of the bottom surface of the tail end of the missile body, the missile body generates downward head lowering moment, and the posture control of the head lowering of the missile body is realized; if the head of the missile body needs to be raised, the regulating valves corresponding to the drainage holes in the lower side surface are opened, and the regulating valves corresponding to the drainage holes in the upper side surface, the left side surface and the right side surface are closed;
if the left deviation of the missile body is to be realized, the regulating valve corresponding to the drainage hole on the right side surface is opened, and the regulating valves corresponding to the drainage holes on the upper side surface, the lower side surface and the left side surface are all closed, at the moment, high-pressure air flows out of the drainage tube on the right side surface, and the pressure near the drainage tube outlet on the right side surface is increased; because the regulating valve corresponding to the drainage hole on the left side surface is closed, the position near the outlet of the drainage pipe on the left side surface is a low-pressure area, and the right side of the bottom surface of the tail end of the missile body is subjected to high pressure, the missile body generates left-biased moment, and the posture control of the left-biased missile body is realized; if the missile body needs to be rightwards deviated, the adjusting valve corresponding to the drainage hole in the left side surface is opened, and the adjusting valve corresponding to the drainage hole in the right side surface is closed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811495836.8A CN109579637B (en) | 2018-12-07 | 2018-12-07 | Missile attitude control mechanism without control surface |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811495836.8A CN109579637B (en) | 2018-12-07 | 2018-12-07 | Missile attitude control mechanism without control surface |
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| CN109579637A CN109579637A (en) | 2019-04-05 |
| CN109579637B true CN109579637B (en) | 2023-04-18 |
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| CN201811495836.8A Active CN109579637B (en) | 2018-12-07 | 2018-12-07 | Missile attitude control mechanism without control surface |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112696978B (en) * | 2020-12-24 | 2022-12-27 | 彩虹无人机科技有限公司 | Small missile ground launching height falling prevention method |
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| CN1430720A (en) * | 2000-05-25 | 2003-07-16 | 斯托姆金属有限公司 | Directional control of missiles |
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| CN105314096A (en) * | 2015-11-12 | 2016-02-10 | 南京航空航天大学 | No-control-surface aircraft with air fed by independent air source |
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| WO1984002974A1 (en) * | 1983-01-19 | 1984-08-02 | Ford Motor Co | Ram air steering system for a guided missile |
| US6840478B2 (en) * | 2002-01-14 | 2005-01-11 | Robert Jonathan Carr | Aircraft internal wing and design |
| FR2924411B1 (en) * | 2007-11-29 | 2010-02-12 | Astrium Sas | REAR DEVICE SPACE BODY |
| CN102951289A (en) * | 2011-08-29 | 2013-03-06 | 顾一明 | Low speed safety aircraft capable of controlling flight attitude by utilizing aerodynamic force |
| CN102649475A (en) * | 2012-04-20 | 2012-08-29 | 徐长法 | Three-hole-seam control airplane |
| CN103057694A (en) * | 2013-01-04 | 2013-04-24 | 北京航空航天大学 | Open type control surface for Coanda effect aircraft |
| CN104787306A (en) * | 2015-03-23 | 2015-07-22 | 顾一明 | Low-speed safety aircraft capable of controlling flight attitude by aerodynamic force |
| CN106184719B (en) * | 2016-09-08 | 2018-10-02 | 中国人民解放军国防科学技术大学 | A kind of porous flow control apparatus applied to hypersonic motor-driven reentry vehicle |
| CN108860597A (en) * | 2018-06-22 | 2018-11-23 | 上海理工大学 | A kind of flapping wings type capacitation device using circulation control lift-rising |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3208383A (en) * | 1963-07-18 | 1965-09-28 | Roland W Larson | Ramjet vent |
| CN1430720A (en) * | 2000-05-25 | 2003-07-16 | 斯托姆金属有限公司 | Directional control of missiles |
| CN102167162A (en) * | 2011-03-10 | 2011-08-31 | 洪瑞庆 | Ultra-high pressure fluid jetting power track transferring system and method for aircraft |
| CN105314096A (en) * | 2015-11-12 | 2016-02-10 | 南京航空航天大学 | No-control-surface aircraft with air fed by independent air source |
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