CN103727849A - Adjustable type control method of antiaircraft missile trajectory-control direct force - Google Patents
Adjustable type control method of antiaircraft missile trajectory-control direct force Download PDFInfo
- Publication number
- CN103727849A CN103727849A CN201410017464.3A CN201410017464A CN103727849A CN 103727849 A CN103727849 A CN 103727849A CN 201410017464 A CN201410017464 A CN 201410017464A CN 103727849 A CN103727849 A CN 103727849A
- Authority
- CN
- China
- Prior art keywords
- jet pipe
- valve
- aperture
- spray pipe
- jet
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Landscapes
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention discloses an adjustable type control method of antiaircraft missile trajectory-control direct force. The method comprises the following steps that a first spray pipe, a second spray pipe, a third spray pipe and a fourth spray pipe are evenly arranged around a combustion chamber of a trajectory-control engine; the first spray pipe and the third spray pipe are placed on the same straight line, the second spray pipe and the fourth spray pipe are placed on the same straight line, and the straight line where the first spray pipe and the third spray pipe are placed is perpendicular to the straight line where the second spray pipe and the fourth spray pipe are placed; a first valve, a second valve, a third valve and a fourth valve are sequentially arranged at the joint of the first spray pipe and the combustion chamber, the joint of the second spray pipe and the combustion chamber, the joint of the third spray pipe and the combustion chamber and the joint of the fourth spray pipe and the combustion chamber respectively; the opening degree of the first spray pipe, the opening degree of the second spray pipe, the opening degree of the third spray pipe and the opening degree of the fourth spray pipe are sequentially controlled through the first valve, the second valve, the third valve and the fourth valve respectively. By the adoption of the adjustable type control method, the size and direction of the trajectory-control direct force which is applied to an antiaircraft missile can be continuously adjusted, and therefore the control precision of the antiaircraft missile is improved.
Description
Technical field
The present invention relates to the rail control Direct Force Control Technology field of air defence missile, particularly a kind of adjustable control method of air defence missile rail control direct force.
Background technology
As everyone knows, along with the increase of height, atmospheric density reduces gradually, and this is the control to air defence missile by impact.In prior art, under pneumatic control mode, the permissible load factor of air defence missile is very little, has affected the maneuverability of air defence missile.For making up air defence missile aerodynamic deficiency when the high-altitude flight, can introduce direct force and control air defence missile, to improve the maneuverability of air defence missile.Solid rail control direct force is one of scheme solving this technical problem.
In prior art, the control method of air defence missile rail control direct force imposes on the constant magnitude of the rail control direct force of air defence missile, and the direction of rail control direct force only only limits to fixing direction, the size that imposes on the rail control direct force of air defence missile cannot regulate, and its direction is also restricted.Therefore, the control method of the air defence missile rail control direct force of prior art is lower to the control accuracy of air defence missile.
Summary of the invention
The object of the invention is the above-mentioned defect for prior art, a kind of adjustable control method of air defence missile rail control direct force is provided.
The adjustable control method of air defence missile rail control direct force provided by the invention comprises the steps:
The first jet pipe, the second jet pipe, the 3rd jet pipe and the 4th jet pipe are arranged at equably to the surrounding of the combustion chamber of rail control engine, the first jet pipe and the 3rd jet pipe are located on the same line, the second jet pipe and the 4th jet pipe are located on the same line, and the straight line at the straight line at the first jet pipe and the 3rd jet pipe place and the second jet pipe and the 4th jet pipe place is perpendicular;
In the junction of the first jet pipe, the second jet pipe, the 3rd jet pipe and the 4th jet pipe and combustion chamber, the first valve, the second valve, the 3rd valve and the 4th valve are set respectively successively;
By the first valve, the second valve, the 3rd valve and the 4th valve, control respectively successively the aperture of the first jet pipe, the second jet pipe, the 3rd jet pipe and the 4th jet pipe, the aperture increase and decrease amplitude of the first jet pipe and the 3rd jet pipe is equated and growth trend contrary, the aperture increase and decrease amplitude of the second jet pipe and the 4th jet pipe equate and growth trend contrary, and the aperture sum of the first jet pipe and the 3rd jet pipe equals the full gate of any one jet pipe at any time, the aperture sum of the second jet pipe and the 4th jet pipe equals the full gate of any one jet pipe at any time.
Preferably, the control of the aperture of the first jet pipe, the second jet pipe, the 3rd jet pipe and the 4th jet pipe is carried out simultaneously.
Preferably, before control engine work, the aperture of the first jet pipe, the second jet pipe, the 3rd jet pipe and the 4th jet pipe is all half aperture in-orbit.
Preferably, the thrust that each jet pipe produces and the aperture of this jet pipe are linearly proportional.
Preferably, the thrust that the first jet pipe, the second jet pipe, the 3rd jet pipe and the 4th jet pipe produce is respectively:
Wherein, T
1be the thrust that the first jet pipe produces; T
2be the thrust that the second jet pipe produces; T
3be the thrust that the 3rd jet pipe produces; T
4be the thrust that the 4th jet pipe produces; T
doublealgebraical sum for the thrust that four jet pipes produce at any time; T is the common rail control direct forces that produce of four jet pipes, and 0≤T≤T
double; χ is the angular bisector of angle and the angle of the common rail control direct forces that produce of four jet pipes of two jet pipes of arbitrary neighborhood, and 360 ° of 0 °≤χ <.
Preferably, when [cos (χ-45 °)] >=0, sign[cos (χ-45 °)] value equal 1; When [cos (χ-45 °)] < 0, sign[cos (χ-45 °)] value equal-1.
The present invention has following beneficial effect:
The adjustable control method of air defence missile rail control direct force of the present invention can realize size and Orientation adjustable continuously of the rail control direct force that imposes on air defence missile, thereby can improve the control accuracy of air defence missile.
Accompanying drawing explanation
Fig. 1 is the flow chart of adjustable control method of the air defence missile rail control direct force of the embodiment of the present invention;
Fig. 2 is the schematic diagram of adjustable control method of the air defence missile rail control direct force of the embodiment of the present invention.
The specific embodiment
Below in conjunction with drawings and Examples, summary of the invention of the present invention is further described.
The adjustable control method of the air defence missile rail control direct force that as shown in Figure 1, the present embodiment provides comprises the steps:
S1: the surrounding that the first jet pipe 2, the second jet pipe 3, the 3rd jet pipe 4 and the 4th jet pipe 5 is arranged at equably to the combustion chamber 1 of rail control engine, the first jet pipe 2 and the 3rd jet pipe 4 are positioned on same straight line EF, the second jet pipe 3 and the 4th jet pipe 5 are positioned on same straight line GH, and the straight line GH at the straight line EF at the first jet pipe 2 and the 3rd jet pipe 4 places and the second jet pipe 3 and the 4th jet pipe 5 places is perpendicular, as shown in Figure 2;
S2: the first valve 6 is set in the first jet pipe 2 and the junction of combustion chamber 1; In the second jet pipe 3 and the junction of combustion chamber 1, the second valve 7 is set; In the 3rd jet pipe 4 and the junction of combustion chamber 1, the 3rd valve 8 is set; In the 4th jet pipe 5 and the junction of combustion chamber 1, the 4th valve 6 is set;
S3: the aperture of controlling the first jet pipe 2 by the first valve 6, by the second valve 7, control the aperture of the second jet pipe 3, by the 3rd valve 8, control the aperture of the 3rd jet pipe 4, by the 4th valve 6, control the aperture of the 4th jet pipe 5, the aperture increase and decrease amplitude of the first jet pipe 2 and the 3rd jet pipe 4 is equated and growth trend contrary, the aperture increase and decrease amplitude of the second jet pipe 3 and the 4th jet pipe 5 equate and growth trend contrary, and the aperture sum of the first jet pipe 2 and the 3rd jet pipe 4 equals the full gate of any one jet pipe at any time, the aperture sum of the second jet pipe 3 and the 4th jet pipe 5 equals the full gate of any one jet pipe at any time, in other words, when the aperture of the first jet pipe 2 increases, corresponding the reducing of aperture of the 3rd jet pipe 4, when the aperture of the 3rd jet pipe 4 increases, corresponding the reducing of aperture of the first jet pipe 2, vice versa, when the aperture of the second jet pipe 3 increases, corresponding the reducing of aperture of the 4th jet pipe 5, when the aperture of the 4th jet pipe 5 increases, corresponding the reducing of aperture of the second jet pipe 3, vice versa.
Before control engine work, the aperture of the first jet pipe 2, the second jet pipe 3, the 3rd jet pipe 4 and the 4th jet pipe 5 is all half aperture in-orbit.
In above-mentioned steps S3, the control of the aperture of four jet pipes is carried out simultaneously, i.e. the control of the aperture of the first jet pipe, the second jet pipe, the 3rd jet pipe and the 4th jet pipe is carried out simultaneously.
In above-mentioned steps S3, the thrust that each jet pipe produces and the aperture of this jet pipe are linearly proportional.
In above-mentioned steps S3, the thrust that the first jet pipe 2, the second jet pipe 3, the 3rd jet pipe 4 and the 4th jet pipe 5 produce is respectively:
In formula (1), T
1be the thrust that the first jet pipe 2 produces; T
2be the thrust that the second jet pipe 3 produces; T
3be the thrust that the 3rd jet pipe 4 produces; T
4be the thrust that the 4th jet pipe 5 produces; T
doublealgebraical sum for the thrust that four jet pipes produce at any time; T is the common rail control direct forces that produce of four jet pipes, and this rail control direct force T is the thrust T that the first jet pipe 2 produces
1, the thrust T that produces of the second jet pipe 3
2, the thrust T that produces of the 3rd jet pipe 4
3thrust T with the 4th jet pipe 5 generations
4vector, this rail control direct force T imposes on air defence missile, and 0≤T≤T
double; χ is the angular bisector of angle and the angle of the common rail control direct force T that produce of four jet pipes of two jet pipes of arbitrary neighborhood, and 360 ° of 0 °≤χ <.
In formula (1), when [cos (χ-45 °)] >=0, sign[cos (χ-45 °)] value equal 1; When [cos (χ-45 °)] < 0, sign[cos (χ-45 °)] value equal-1.
In the present embodiment, the angular bisector of the angle of the first jet pipe 2 and the 4th jet pipe 5 is straight line OB; The angular bisector of the angle of the first jet pipe 2 and the second jet pipe 3 is straight line OC; The angular bisector of the angle of the second jet pipe 3 and the 3rd jet pipe 4 is straight line OA; The angular bisector of the angle of the 3rd jet pipe 4 and the 4th jet pipe 5 is straight line OD.For example the angular bisector OB of the angle of the first jet pipe 2 and the 4th jet pipe 5 is labeled as to reference line.The direction of four common rail control direct force T that produce of jet pipe is straight line OP direction.Four the common direction of rail control direct force T and angles of reference line that produce of jet pipe are χ, and the angle between straight line OP and reference line OB is χ.
The adjustable control method of the air defence missile rail control direct force of the present embodiment can realize size and Orientation adjustable continuously of the rail control direct force that imposes on air defence missile, thereby can improve the control accuracy of air defence missile.
Should be appreciated that the above detailed description of technical scheme of the present invention being carried out by preferred embodiment is illustrative and not restrictive.Those of ordinary skill in the art modifies reading the technical scheme that can record each embodiment on the basis of description of the present invention, or part technical characterictic is wherein equal to replacement; And these modifications or replacement do not make the essence of appropriate technical solution depart from the spirit and scope of various embodiments of the present invention technical scheme.
Claims (6)
1. an adjustable control method for air defence missile rail control direct force, is characterized in that, this adjustable control method comprises the steps:
The first jet pipe, the second jet pipe, the 3rd jet pipe and the 4th jet pipe are arranged at equably to the surrounding of the combustion chamber of rail control engine, the first jet pipe and the 3rd jet pipe are located on the same line, the second jet pipe and the 4th jet pipe are located on the same line, and the straight line at the straight line at the first jet pipe and the 3rd jet pipe place and the second jet pipe and the 4th jet pipe place is perpendicular;
In the junction of the first jet pipe, the second jet pipe, the 3rd jet pipe and the 4th jet pipe and combustion chamber, the first valve, the second valve, the 3rd valve and the 4th valve are set respectively successively;
By the first valve, the second valve, the 3rd valve and the 4th valve, control respectively successively the aperture of the first jet pipe, the second jet pipe, the 3rd jet pipe and the 4th jet pipe, the aperture increase and decrease amplitude of the first jet pipe and the 3rd jet pipe is equated and growth trend contrary, the aperture increase and decrease amplitude of the second jet pipe and the 4th jet pipe equate and growth trend contrary, and the aperture sum of the first jet pipe and the 3rd jet pipe equals the full gate of any one jet pipe at any time, the aperture sum of the second jet pipe and the 4th jet pipe equals the full gate of any one jet pipe at any time.
2. the adjustable control method of air defence missile rail control direct force according to claim 1, is characterized in that, the control of the aperture of the first jet pipe, the second jet pipe, the 3rd jet pipe and the 4th jet pipe is carried out simultaneously.
3. the adjustable control method of air defence missile rail control direct force according to claim 1, is characterized in that, before control engine work, the aperture of the first jet pipe, the second jet pipe, the 3rd jet pipe and the 4th jet pipe is all half aperture in-orbit.
4. the adjustable control method of air defence missile rail control direct force according to claim 1, is characterized in that, the thrust that each jet pipe produces and the aperture of this jet pipe are linearly proportional.
5. the adjustable control method of air defence missile rail control direct force according to claim 1, is characterized in that, the thrust that the first jet pipe, the second jet pipe, the 3rd jet pipe and the 4th jet pipe produce is respectively:
Wherein, T
1be the thrust that the first jet pipe produces; T
2be the thrust that the second jet pipe produces; T
3be the thrust that the 3rd jet pipe produces; T
4be the thrust that the 4th jet pipe produces; T
doublealgebraical sum for the thrust that four jet pipes produce at any time; T is the common rail control direct forces that produce of four jet pipes, and 0≤T≤T
double; χ is the angular bisector of angle and the angle of the common rail control direct forces that produce of four jet pipes of two jet pipes of arbitrary neighborhood, and 360 ° of 0 °≤χ <.
6. the adjustable control method of air defence missile rail control direct force according to claim 5, is characterized in that, when the value of [during cos (χ-45 °) >=0, sign[cos (χ-45 °)] equals 1; When [cos (χ-45 °)] < 0, sign[cos (χ-45 °)] value equal-1.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410017464.3A CN103727849A (en) | 2014-01-14 | 2014-01-14 | Adjustable type control method of antiaircraft missile trajectory-control direct force |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410017464.3A CN103727849A (en) | 2014-01-14 | 2014-01-14 | Adjustable type control method of antiaircraft missile trajectory-control direct force |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103727849A true CN103727849A (en) | 2014-04-16 |
Family
ID=50452031
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410017464.3A Pending CN103727849A (en) | 2014-01-14 | 2014-01-14 | Adjustable type control method of antiaircraft missile trajectory-control direct force |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103727849A (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1430720A (en) * | 2000-05-25 | 2003-07-16 | 斯托姆金属有限公司 | Directional control of missiles |
| CN200964906Y (en) * | 2006-10-13 | 2007-10-24 | 中国北方工业公司 | Terminal guided fodder impulse correction engine |
| CN103512438A (en) * | 2013-10-25 | 2014-01-15 | 北京电子工程总体研究所 | Adjustable control method for orbit control direct force on air-defense missile |
-
2014
- 2014-01-14 CN CN201410017464.3A patent/CN103727849A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1430720A (en) * | 2000-05-25 | 2003-07-16 | 斯托姆金属有限公司 | Directional control of missiles |
| CN200964906Y (en) * | 2006-10-13 | 2007-10-24 | 中国北方工业公司 | Terminal guided fodder impulse correction engine |
| CN103512438A (en) * | 2013-10-25 | 2014-01-15 | 北京电子工程总体研究所 | Adjustable control method for orbit control direct force on air-defense missile |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105182984B (en) | The linear active disturbance rejection controller design and parameter tuning method of aircraft pitch attitude | |
| CN103512438A (en) | Adjustable control method for orbit control direct force on air-defense missile | |
| CN107401956A (en) | Amphibious cruise missile and its attitude control method based on venturi offset fluidic vectoring nozzle | |
| CN105867399B (en) | Method for determining multi-state tracking guidance parameters | |
| CN103899433A (en) | Novel thrust vectoring nozzle structure adopting shock vectoring controlling | |
| CN102302989A (en) | Supersonic velocity spray pipe with shared throat part and design method of supersonic velocity spray pipe | |
| US20180363645A1 (en) | Valve Adapter Connection Assembly | |
| CN106527128B (en) | Take into account the Flight Control Law design method of transient response and robust stability | |
| CN110645118B (en) | Equal-flow solid attitude control thrust device and design method | |
| CN104949283B (en) | The air-valve adjusting method and system of a kind of control air quantity | |
| CN103727849A (en) | Adjustable type control method of antiaircraft missile trajectory-control direct force | |
| CN105257758B (en) | A kind of control method of variable auxiliary chamber air spring constructions | |
| CN108801081B (en) | Nonsingular rolling instruction generation algorithm for BTT missile | |
| CN106768803B (en) | A kind of pneumatic jet pipe in subsonic speed circle turn side | |
| CN117369509A (en) | Aircraft guidance control integrated design method based on preset performance | |
| He et al. | Sliding mode-based continuous guidance law with terminal angle constraint | |
| Qian et al. | SDRE based impact angle control guidance law considering seeker's field-of-view limit | |
| CN204239781U (en) | A kind of novel butterfly valve with hyperbolic formula port plate | |
| CN106773701B (en) | A kind of real-time optimization method of control channel rudder instruction clipping | |
| Golestani et al. | Fractional order sliding mode guidance law: Improving performance and robustness | |
| CN103757610B (en) | A kind of process environments pressure dispatching method based on material suppling system model | |
| FR3041999B1 (en) | METHOD FOR LIMITING THE RECIRCULATED GAS RATE FOR A PHASE-PHASE ENGINE DURING A TRANSIENT AIR LOAD PHASE | |
| CN105056667A (en) | Pressure-stabilizing aerial fog distributor | |
| 김효영 et al. | Design of a voice coil motor for active vibration isolator of CFRP high speed inspection system | |
| CN117537670B (en) | Rudder distribution method for improving remote missile rudder resource utilization efficiency |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C12 | Rejection of a patent application after its publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20140416 |