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 PDF

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CN103727849A
CN103727849A CN 201410017464 CN201410017464A CN103727849A CN 103727849 A CN103727849 A CN 103727849A CN 201410017464 CN201410017464 CN 201410017464 CN 201410017464 A CN201410017464 A CN 201410017464A CN 103727849 A CN103727849 A CN 103727849A
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nozzle
valve
spray pipe
control
force
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CN 201410017464
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Chinese (zh)
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郑咏岚
钟凌伟
邹忠望
李向林
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北京电子工程总体研究所
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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

一种防空导弹轨控直接力的可调式控制方法 Adjustable orbit control method for controlling a direct anti-aircraft missile force

技术领域 FIELD

[0001] 本发明涉及防空导弹的轨控直接力控制技术领域,特别涉及一种防空导弹轨控直接力的可调式控制方法。 [0001] Direct force orbit control of the present invention relates to anti-aircraft missile control technology, and particularly relates to a method of controlling the adjustable air missile orbit control forces directly.

背景技术 Background technique

[0002] 众所周知,随着高度的增加,大气密度逐渐降低,这将影响对防空导弹的控制。 [0002] It is well known as the height increases, air density decreases, which will affect the control of anti-aircraft missiles. 现有技术中,气动控制方式下防空导弹的可用过载很小,影响了防空导弹的机动能力。 Available prior art overload small, pneumatically under control of anti-aircraft missiles, influence the mobility SAM. 为弥补防空导弹在高空飞行时空气动力的不足,可引入直接力来控制防空导弹,以提高防空导弹的机动能力。 To compensate for lack of anti-aircraft missile aerodynamics of flying at high altitude, it can be introduced directly force to control anti-aircraft missiles, anti-aircraft missiles to enhance the mobility of. 固体轨控直接力即是解决该技术问题的方案之一。 Solid Divert direct force that is one solution to this technical problem.

[0003] 现有技术中,防空导弹轨控直接力的控制方法施加给防空导弹的轨控直接力的大小恒定,且轨控直接力的方向仅仅限于固定的方向,即施加给防空导弹的轨控直接力的大小无法调节,其方向也受到限制。 Direct size orbit control force [0003] In the prior art, direct anti-aircraft missiles orbit control method of controlling the force applied to the anti-aircraft missiles constant, and the direction of orbit control force directly limited to a fixed direction, i.e., applied to anti-aircraft missiles tracks direct control of the size of the force can not be adjusted, which direction is also restricted. 因此,现有技术的防空导弹轨控直接力的控制方法对防空导弹的控制精度较低。 Thus, the prior art air defense missile orbit control method for controlling the direct power control accuracy is low SAM.

发明内容 SUMMARY

[0004] 本发明的目的是针对现有技术的上述缺陷,提供一种防空导弹轨控直接力的可调式控制方法。 [0004] The object of the present invention is directed to the above-described drawbacks of the prior art, to provide a direct anti-aircraft missiles orbit control method for controlling an adjustable force.

[0005] 本发明提供的防空导弹轨控直接力的可调式控制方法包括如下步骤: [0005] The method of controlling the adjustable air defense missile orbit control of the present invention provides a direct force comprises the steps of:

[0006] 将第一喷管、第二喷管、第三喷管和第四喷管均匀地设置于轨控发动机的燃烧室的四周,第一喷管和第三喷管位于同一条直线上,第二喷管和第四喷管位于同一条直线上,且第一喷管和第三喷管所在的直线与第二喷管和第四喷管所在的直线相垂直; [0006] The first nozzle, the second nozzle, third nozzle and the fourth nozzle disposed uniformly in four weeks orbit control engine combustion chamber, a first nozzle and the third nozzle positioned on the same line , the second nozzle and the fourth nozzle positioned on the same line, and the first nozzle and the third straight line where the straight line of the second nozzle and the fourth nozzle located perpendicular to the nozzle;

[0007] 在第一喷管、第二喷管、第三喷管和第四喷管与燃烧室的连接处依次分别设置第一阀门、第二阀门、第三阀门和第四阀门; [0007] In a first nozzle, a second nozzle, third nozzle and the fourth nozzle connected to the combustion chamber are sequentially provided a first valve, the second valve, the third valve and a fourth valve;

[0008] 通过第一阀门、第二阀门、第三阀门和第四阀门依次分别控制第一喷管、第二喷管、第三喷管和第四喷管的开度,使得第一喷管与第三喷管的开度增减幅度相等且增减趋势相反,第二喷管与第四喷管的开度增减幅度相等且增减趋势相反,且在任意时刻第一喷管与第三喷管的开度之和等于任意一个喷管的全开度,在任意时刻第二喷管与第四喷管的开度之和等于任意一个喷管的全开度。 [0008] through the first valve, the second valve, the third valve and the fourth valve are sequentially control the first nozzle, the nozzle opening degree of the second, third and fourth nozzles of the nozzle, such that the first nozzle equal to the third nozzle opening degree of the increase or decrease contrast and decrease trend, increase or decrease the degree of opening of the second nozzle and the fourth nozzle equal and opposite increase or decrease trend, and the first and the second nozzle at any time ter nozzle opening degree is equal to any of a wide open nozzle, at any time the degree of opening of the second nozzle and the fourth nozzle and is equal to any of a wide open nozzle.

[0009] 优选地,第一喷管、第二喷管、第三喷管和第四喷管的开度的控制同时进行。 [0009] Preferably, the first nozzle, the second nozzle, third nozzle and the fourth nozzle opening degree control simultaneously.

[0010] 优选地,在轨控发动机工作之前,第一喷管、第二喷管、第三喷管和第四喷管的开度都为半开度。 [0010] Preferably, before the orbit control operation of the engine, a first nozzle, a second nozzle, third nozzle and the fourth nozzle opening degree are half opened degree.

[0011] 优选地,每一个喷管产生的推力与该喷管的开度成线性比例关系。 [0011] Preferably, the degree of opening of each of the nozzle to produce thrust nozzle linearly proportional.

[0012] 优选地,第一喷管、第二喷管、第三喷管和第四喷管产生的推力分别为: [0012] Preferably, the first thrust nozzle, the second nozzle, third nozzle and the fourth nozzle to produce respectively:

[0013] [0013]

士昏卜0七_45。 Bu Shi faint 0 seven _45. )| ) |

Figure CN103727849AD00041

[0017] 其中,T1为第一喷管产生的推力;T2为第二喷管产生的推力;Τ3为第三喷管产生的推力;τ4为第四喷管产生的推力汀—为在任意时刻四个喷管产生的推力的代数和汀为四个喷管共同产生的轨控直接力,且O < T ≤ Tdouble ; X为任意相邻的两个喷管的夹角的角平分线与四个喷管共同产生的轨控直接力的夹角,且0° ≤ X < 360°。 [0017] wherein, T1 is the thrust generated by a first nozzle; T2 thrust generated by the second nozzle; tau] 3 of the third nozzle thrust generated; [tau] 4 is a fourth thrust nozzle statin produced - at any time of four nozzles generating thrust algebraic orbit control and direct the force statin is co-produced four nozzles, and O <T ≤ Tdouble; X is any two adjacent nozzle angle bisector and four angle of orbit control direct a force generated by a common nozzle, and 0 ° ≤ X <360 °.

[0018]优选地,当[cos ( X -45 ° )]≤ O 时,sign [cos ( x -45 ° )]的值等于I ;当[cos ( X -45° ) ] < O 时,sign [cos ( X-45° )]的值等于-1。 [0018] Preferably, when the [cos (X -45 °)] When ≤ O, the value sign [cos (x -45 °)] is equal to I; when [cos (X -45 °)] <O, sign value [cos (X-45 °)] is equal to -1.

[0019] 本发明具有如下有益效果: [0019] The present invention has the following advantages:

[0020] 本发明的防空导弹轨控直接力的可调式控制方法能够实现施加给防空导弹的轨控直接力的大小和方向的连续可调,从而能够提高防空导弹的控制精度。 [0020] The method of controlling the adjustable air defense missile orbit control forces directly to the present invention can be implemented continuously adjustable direct force applied to the orbit control of anti-aircraft missiles magnitude and direction, it is possible to improve the control accuracy SAM.

附图说明 BRIEF DESCRIPTION

[0021] 图1为本发明实施例的防空导弹轨控直接力的可调式控制方法的流程图; Adjustable flow chart of a control method of [0021] Figure 1 is a direct anti-aircraft missile force orbit control of the embodiment of the present invention;

[0022] 图2为本发明实施例的防空导弹轨控直接力的可调式控制方法的示意图。 Adjustable schematic diagram of a control method [0022] FIG. 2 is a direct anti-aircraft missile force orbit control of the embodiment of the present invention.

具体实施方式 detailed description

[0023] 下面结合附图及实施例对本发明的发明内容作进一步的描述。 [0023] Example embodiments of the present invention will be further described below in conjunction with the accompanying drawings and.

[0024] 如图1所示,本实施例提供的防空导弹轨控直接力的可调式控制方法包括如下步骤: Adjustable control method [0024] shown in FIG. 1, and orbit control force provided by a direct anti-aircraft missiles of the present embodiment comprises the following steps:

[0025] S1:将第一喷管2、第二喷管3、第三喷管4和第四喷管5均匀地设置于轨控发动机的燃烧室I的四周,第一喷管2和第三喷管4位于同一条直线EF上,第二喷管3和第四喷管5位于同一条直线GH上,且第一喷管2和第三喷管4所在的直线EF与第二喷管3和第四喷管5所在的直线GH相垂直,如图2所示; [0025] S1: 2 of the first nozzle, the second nozzle 3, the third and fourth nozzles 4 disposed in the injection nozzle 5 uniformly four weeks orbit control engine combustion chamber I, a first and second spout 2 three nozzles 4 located on the same straight line EF, a second nozzle and the fourth nozzle 3 5 located on the same straight line GH, EF and where the first straight line and the third nozzle spout 2 and the second nozzles 4 3 and a fourth straight line is located perpendicular to the nozzle 5 GH, shown in Figure 2;

[0026] S2:在第一喷管2与燃烧室I的连接处设置第一阀门6 ;在第二喷管3与燃烧室I的连接处设置第二阀门7 ;在第三喷管4与燃烧室I的连接处设置第三阀门8 ;在第四喷管5与燃烧室I的连接处设置第四阀门6 ; [0026] S2: a first nozzle 2 is provided with a first valve connected to the combustion chamber 6 I; a second nozzle connected to the combustion chamber 3 and I 7 provided in the second valve; and the third nozzle 4 I connected to the combustion chamber is provided a third valve 8; fourth valve provided at the connection of the combustion chamber 6 in a fourth nozzle 5 I;

[0027] S3:通过第一阀门6控制第一喷管2的开度,通过第二阀门7控制第二喷管3的开度,通过第三阀门8控制第三喷管4的开度,通过第四阀门6控制第四喷管5的开度,使得第一喷管2与第三喷管4的开度增减幅度相等且增减趋势相反,第二喷管3与第四喷管5的开度增减幅度相等且增减趋势相反,且在任意时刻第一喷管2与第三喷管4的开度之和等于任意一个喷管的全开度,在任意时刻第二喷管3与第四喷管5的开度之和等于任意一个喷管的全开度;换言之,第一喷管2的开度增大时,第三喷管4的开度相应减小,第三喷管4的开度增大时,第一喷管2的开度相应减小,反之亦然;第二喷管3的开度增大时,第四喷管5的开度相应减小,第四喷管5的开度增大时,第二喷管3的开度相应减小,反之亦然。 [0027] S3: controlling the degree of opening of the first nozzle 2 through the first valve 6, opening of the second nozzle 3 through the second control valve 7, the opening degree of the third nozzle 4 is controlled by a third valve 8, by the fourth control valve 6 of the fourth nozzle opening 5, so that the increase or decrease in the degree of opening of the first nozzle and the third nozzle 2 4 equal and opposite changes in the trend, the second nozzle and the fourth nozzle 3 increase or decrease the degree of opening 5 equal and opposite increase or decrease trend, and the first and the third nozzle 2 and the nozzle opening degree of a nozzle 4 is equal to any of the fully open at any time, at any time of the second discharge tube and 3 degrees and the fourth nozzle opening 5 is equal to any of a wide open nozzle; in other words, when the opening of the first nozzle 2 is increased, the opening degree of the third nozzle 4 is correspondingly reduced section when the opening degree of the three nozzle 4 is increased, the opening degree of the first nozzle tube 2 is reduced correspondingly, and vice versa; when the degree of opening of the second nozzle 3 is increased, the opening degree of the nozzle 5 in a corresponding decrease in the fourth when the opening degree of the fourth nozzle 5 increases, the degree of opening of the second nozzle 3 is correspondingly reduced, and vice versa.

[0028] 在轨控发动机工作之前,第一喷管2、第二喷管3、第三喷管4和第四喷管5的开度都为半开度。 [0028] Before orbit control operation of the engine, a first spout 2, 3 of the second nozzle, third nozzle opening degree of the nozzles 4 and 5 are a fourth half-opening degree.

[0029] 在上述步骤S3中,四个喷管的开度的控制同时进行,即第一喷管、第二喷管、第三喷管和第四喷管的开度的控制同时进行。 [0029] In the step S3, the opening degree of the nozzle four simultaneously, i.e. a first nozzle, a second nozzle, third nozzle and the fourth nozzle opening degree control simultaneously.

[0030] 在上述步骤S3中,每一个喷管产生的推力与该喷管的开度成线性比例关系。 [0030] In the above step S3, the thrust generated by each nozzle is linearly proportional to the degree of opening of the nozzle.

[0031] 在上述步骤S3中,第一喷管2、第二喷管3、第三喷管4和第四喷管5产生的推力 Thrust [0031] In step S3, the first nozzle tube 2, a second nozzle 3, the third and fourth nozzles 4 of the nozzle 5 generates

分别为: They are as follows:

Figure CN103727849AD00051

[0036] 公式⑴中,T1为第一喷管2产生的推力;T2为第二喷管3产生的推力;Τ3为第三喷管4产生的推力;Τ4为第四喷管5产生的推力;Τ—为在任意时刻四个喷管产生的推力的代数和;Τ为四个喷管共同产生的轨控直接力,该轨控直接力T为第一喷管2产生的推力T1、第二喷管3产生的推力T2、第三喷管4产生的推力T3和第四喷管5产生的推力T4的矢量和,该轨控直接力T施加给防空导弹,且O < T < Tdouble ; X为任意相邻的两个喷管的夹角的角平分线与四个喷管共同产生的轨控直接力T的夹角,且0° ( X < 360°。 [0036] Equation ⑴, T1 was the thrust generated by a first nozzle 2; T2 thrust generated by the second nozzle 3; tau] 3 is the thrust generated by the third nozzle 4; [tau] 4 is a fourth force generated by the nozzle 5 ; tau-four nozzles at any time is a thrust generated by the algebraic sum; Τ for the orbit control force directly co-produced four nozzles, which direct orbit control thrust force T generated T1 of the first nozzle 2, the first 3 two nozzle thrust generated T2, vector the thrust generated by the third nozzle 4 T3 and fourth T4 thrust generated by the injection nozzle 5 and the orbit control force T is applied directly to the missile, and O <T <Tdouble; direct force orbit control angle T is X is any two adjacent nozzle angle bisector co-produced with four nozzles, and 0 ° (X <360 °.

[0037]公式⑴中,当[cos ( X-45 ° )]≥ O 时,sign[cos ( X-45 ° )]的值等于I;当[cos ( X -45° ) ] < O 时,sign [cos ( X-45° )]的值等于-1。 [0037] In the formula ⑴, when [cos (-45 X °)] ≥ O, sign [cos (-45 X °)] is equal to I; when [cos (X -45 °)] <O, the value sign [cos (X-45 °)] is equal to -1.

[0038] 在本实施例中,第一喷管2与第四喷管5的夹角的角平分线为直线OB ;第一喷管2与第二喷管3的夹角的角平分线为直线OC ;第二喷管3与第三喷管4的夹角的角平分线为直线OA ;第三喷管4与第四喷管5的夹角的角平分线为直线0D。 [0038] In the present embodiment, the first nozzle angle bisector 2 fourth nozzle 5 is linear the OB; a first nozzle 2 and the second nozzle angle is the angle bisector 3 linear -OC; second nozzle 3 and the angle bisector of the third linear nozzle 4 is OA; the third angle and the fourth nozzles 4 of the nozzle 5 bisector linearly 0D. 例如将第一喷管2与第四喷管5的夹角的角平分线OB标记为参考线。 For example the angle between the first nozzle and the fourth nozzle 2 5 bisector line OB reference marker. 四个喷管共同产生的轨控直接力T的方向为直线OP方向。 The direction of orbit control force T of four nozzles direct co-produced OP a linear direction. 四个喷管共同产生的轨控直接力T的方向与参考线的夹角为X,即直线OP与参考线OB之间的夹角为X。 Angle of orbit control and direct force T and the reference direction of the nozzle line four co-produced as X, i.e. the angle between the reference line and the straight line OP OB is X.

[0039] 本实施例的防空导弹轨控直接力的可调式控制方法能够实现施加给防空导弹的轨控直接力的大小和方向的连续可调,从而能够提高防空导弹的控制精度。 Adjustable continuous adjustable control method [0039] The present embodiment air missile orbit control can be achieved directly orbit control force directly applied to anti-aircraft missiles force magnitude and direction, it is possible to improve the control accuracy SAM.

[0040] 应当理解,以上借助优选实施例对本发明的技术方案进行的详细说明是示意性的而非限制性的。 [0040] It should be understood that the foregoing detailed description is illustrative and not limiting examples of preferred embodiments of the aspect of the present invention by means of. 本领域的普通技术人员在阅读本发明说明书的基础上可以对各实施例所记载的技术方案进行修改,或者对其中部分技术特征进行等同替换;而这些修改或者替换,并不使相应技术方案的本质脱离本发明各实施例技术方案的精神和范围。 Those of ordinary skill in the art upon reading the specification may be performed on the basis of the present invention, the technical solutions described in each of the modified embodiments, some technical features or equivalent replacements; such modifications or replacements do not cause the corresponding technical solutions departing from the essence of the present invention, various embodiments spirit and scope of the technical solutions.

Claims (6)

  1. 1.一种防空导弹轨控直接力的可调式控制方法,其特征在于,该可调式控制方法包括如下步骤: 将第一喷管、第二喷管、第三喷管和第四喷管均匀地设置于轨控发动机的燃烧室的四周,第一喷管和第三喷管位于同一条直线上,第二喷管和第四喷管位于同一条直线上,且第一喷管和第三喷管所在的直线与第二喷管和第四喷管所在的直线相垂直; 在第一喷管、第二喷管、第三喷管和第四喷管与燃烧室的连接处依次分别设置第一阀门、第二阀门、第三阀门和第四阀门; 通过第一阀门、第二阀门、第三阀门和第四阀门依次分别控制第一喷管、第二喷管、第三喷管和第四喷管的开度,使得第一喷管与第三喷管的开度增减幅度相等且增减趋势相反,第二喷管与第四喷管的开度增减幅度相等且增减趋势相反,且在任意时刻第一喷管与第三喷管的开度之和等于任意 A direct anti-aircraft missiles orbit control method for controlling an adjustable force, characterized in that the adjustable control method comprising the steps of: a first nozzle, a second nozzle, third nozzle and the fourth nozzle uniformly a combustion chamber disposed in the orbit control of the engine around the first nozzle and the third nozzle positioned on the same line, a second nozzle and the fourth nozzle positioned on the same line, and the first and third nozzle straight nozzle where the nozzle and the second straight line located perpendicular to the fourth nozzle; a first nozzle, a second nozzle, third nozzle and the fourth nozzle connected to the combustion chamber are provided sequentially first valve, the second valve, the third valve and a fourth valve; through a first valve, the second valve, the third valve and the fourth valve are sequentially control the first nozzle, the second nozzle, third nozzle and equal to the fourth degree of opening of the nozzle, such that the first nozzle and the third nozzle opening degree of the increase or decrease contrast and decrease trend, increase or decrease the degree of opening is equal to the second nozzle and the fourth nozzle and decrease Instead trend, and at any time of the first nozzle and the third nozzle opening degrees and equal to any 个喷管的全开度,在任意时刻第二喷管与第四喷管的开度之和等于任意一个喷管的全开度。 Full of a nozzle, at any time the degree of opening of the second nozzle and the fourth nozzle and is equal to any of a wide open nozzle.
  2. 2.根据权利要求1所述的防空导弹轨控直接力的可调式控制方法,其特征在于,第一喷管、第二喷管、第三喷管和第四喷管的开度的控制同时进行。 The anti-aircraft missiles adjustable according to a control method of orbit control force directly claim, wherein the opening degree of the first nozzle, the second nozzle, third nozzle and the fourth nozzle while get on.
  3. 3.根据权利要求1所述的防空导弹轨控直接力的可调式控制方法,其特征在于,在轨控发动机工作之前,第一喷管、第二喷管、第三喷管和第四喷管的开度都为半开度。 The adjustable control method according to a direct anti-aircraft missile force orbit control as claimed in claim, characterized in that the orbit control operation of the engine before the first nozzle, the second nozzle, third and fourth spray nozzles the degree of opening of both half tube opening.
  4. 4.根据权利要求1所述的防空导弹轨控直接力的可调式控制方法,其特征在于,每一个喷管产生的推力与该喷管的开度成线性比例关系。 The control of the air defense missile track control method for a direct force adjustable according to claim, characterized in that the thrust generated by each of the nozzle opening degree of the nozzle is linearly proportional.
  5. 5.根据权利要求1所述的防空导弹轨控直接力的可调式控制方法,其特征在于,第一喷管、第二喷管、第三喷管和第四喷管产生的推力分别为: The adjustable control method according to a direct anti-aircraft missile force orbit control as claimed in claim, wherein the first thrust nozzle, the second nozzle, third nozzle and the fourth nozzle to produce respectively:
    Figure CN103727849AC00021
    其中,T1为第一喷管产生的推力;τ2为第二喷管产生的推力;τ3为第三喷管产生的推力;Τ4为第四喷管产生的推力;Τ—为在任意时刻四个喷管产生的推力的代数和;τ为四个喷管共同产生的轨控直接力,且O < T ( Tdouble ; X为任意相邻的两个喷管的夹角的角平分线与四个喷管共同产生的轨控直接力的夹角,且0° ( X < 360°。 Wherein, T1 is the thrust generated by a first nozzle; [tau] 2 of the second nozzle thrust generated; tau] 3 of the third nozzle thrust generated; [tau] 4 is a fourth force generated by the nozzle; at any time is tau-four algebraic thrust generated and the nozzle; [tau] is a direct orbit control force generated by the four common nozzle, and O <T (Tdouble; X is the angle between any adjacent two nozzles and four angle bisector angle of the nozzle orbit control force directly co-produced, and 0 ° (X <360 °.
  6. 6.根据权利要求5所述的防空导弹轨控直接力的可调式控制方法,其特征在于,当[cos ( X -45。)> O 时,sign [cos ( x -45。)]的值等于I ;当[cos ( x -45。)] < O 时,sign[cos ( X -45° )]的值等于-1。 5 according to the air defense missile adjustable orbit control method for controlling a force directly claim, wherein, when the [cos (X -45.)> O, the value sign [cos (x -45.)] In It is equal to I; [(. x -45) cos] when <time O, the value sign [cos (X -45 °)] is equal to -1.
CN 201410017464 2014-01-14 2014-01-14 Adjustable type control method of antiaircraft missile trajectory-control direct force CN103727849A (en)

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Citations (3)

* Cited by examiner, † Cited by third party
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

Patent Citations (3)

* Cited by examiner, † Cited by third party
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

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