A Design Method for Curvilinear Range-Increasing Trajectory in the Midcourse Guidance Phase

Abstract

The present invention discloses a method for designing a curved range-increasing trajectory in the mid-course guidance section, belonging to the field of guidance technology, and is applicable to a simple, highly versatile, and engineering-applicable method for designing a curved range-increasing trajectory of a medium- and long-range anti-tank missile using inertial guidance in the mid-course guidance section. Based on the information output by inertial navigation and combined with target information, this method determines the desired altitude trajectory in the mid-course guidance section. A method for solving the desired altitude trajectory in the mid-course guidance section that takes into account both range increase and terminal velocity requirements is provided. This method is characterized by simplicity, strong versatility, and suitability for engineering applications, and has broad application value in similar medium- and long-range anti-tank missile systems. The present invention has been applied in the development process of a certain domestic missile weapon system.

Description

Technical Field

[0001] The present invention belongs to the field of guidance technology and is applicable to medium and long-range anti-tank missiles that use inertial guidance in the mid-course guidance section and have the requirement of over-the-horizon attack. It is mainly used for the design of the desired altitude trajectory during the flight of the missile in the mid-course guidance section, and can take into account the requirements of range and terminal velocity. Background Art

[0002] Due to the strict limitation of the size of the missile seeker and its limited operating range, medium and long-range anti-tank missiles usually adopt a combined guidance system of mid-course inertial guidance and terminal active guidance to meet the requirement of over-the-horizon attack. Medium and long-range anti-tank missiles do not have a ramjet engine that can provide long-term thrust, and the range must be increased through the optimized design of the trajectory.

[0003] Some studies have shown that increasing the missile flight trajectory can effectively increase its range. The higher the missile flight altitude, the lower the atmospheric density, the smaller the aerodynamic drag, and the longer the missile can fly and the farther the target it can attack. In a domestic research model, there are requirements for long range and high terminal velocity. Especially when a straight trajectory is adopted in the mid-course guidance section, the engine endurance cannot meet the requirement of the farthest range.

[0004] Therefore, it is necessary to design a reasonable and feasible altitude trajectory for the mid-course guidance section to give full play to the working ability of the engine and maximize the missile range on the premise of meeting the terminal velocity requirement. Summary of the Invention

[0005] The technical problem to be solved by the present invention is to maximize the missile range under the requirement of a certain terminal velocity; design a reasonable and feasible altitude trajectory for the mid-course guidance section to give full play to the working ability of the engine and maximize the missile range on the premise of meeting the terminal velocity requirement.

[0006] That is, a method for designing a mid-course curved range-increasing trajectory during the flight of a medium and long-range anti-tank missile is provided, which can take into account the requirements of range and terminal velocity.

[0007] In addition, adopting a high-trajectory ballistic in the mid-course guidance section can utilize the characteristic of relatively small aerodynamic drag in the high-altitude environment to effectively reduce the speed loss of medium and long-range anti-tank missiles. The present invention provides a high-trajectory ballistic design method for the mid-course guidance section of medium and long-range anti-tank missiles, which is easy to implement, has strong versatility, and has wide popularization value.

[0008] The technical solution of the present invention is as follows:

[0009] A method for designing a mid-course curved range-increasing trajectory, characterized in that the method comprises the following steps:

[0010] Step 1: Obtain the inertial navigation output information;

[0011] Step 2: Obtain the target information;

[0012] Step 3: First, obtain the position at the starting moment of missile altitude control based on the information output by the inertial navigation, and at the same time obtain the position of the target according to the target information, and then determine the arc-shaped curve extended-range trajectory, that is, determine the expected trajectory DeH of the missile in the mid-course guidance section:

[0013] DeH = DR2 + b;

[0014] The specific solution of the parameters involved is as follows:

[0015]

[0016]

[0017]

[0018] Among them, hx0 and hy0 are the X-direction position and Y-direction position of the missile at the starting moment of altitude control; Xt and Yt are the X-direction position and Y-direction position of the target, and DR0 is the missile-target distance at the starting moment of altitude control;

[0019] R is the curve extended-range adjustment parameter. Determine the value of R to obtain the expected trajectory of the missile.

[0020] Furthermore, continuously adjust the value of R to obtain the expected trajectory of the missile that meets the requirements.

[0021] Furthermore, the initial value of R is taken as 0.5DR0; where DR0 is the missile-target distance at the starting moment of altitude control.

[0022] Furthermore,

[0023] Furthermore, based on the initial value of R, 0.5DR0; increase or decrease the value of R so that the terminal velocity of the trajectory meets the requirements; at this time, it is the determined trajectory.

[0024] The principle of the present invention is:

[0025] First, analyze the factors affecting the range and terminal velocity of medium and long-range anti-tank missiles, and then, based on the information output by the inertial navigation and combined with the target information, conduct a detailed derivation and description of the calculation process of the expected altitude trajectory in the mid-course guidance section. Finally, take the straight-line trajectory as an example to analyze the feasibility and advantages of the curve extended-range trajectory designed by the present invention.

[0026] The beneficial effects of the present invention:

[0027] This method has the characteristics of simple calculation, strong versatility and suitability for engineering applications, and has wide application value in similar medium- and long-range anti-tank missile systems. The present invention has been applied in the development process of a certain domestic anti-tank missile weapon system. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 X-Y Trajectory Comparison (40000m Target)

[0029] Figure 2 Flight Speed Comparison (40000m Target)

[0030] Figure 3 X-Y Trajectory Comparison (50000m Target)

[0031] Figure 4 Flight Speed Comparison (50000m Target)

[0032] Figure 5 X-Y Trajectory Comparison (55000m Target)

[0033] Figure 6 Flight Speed Comparison (55000m Target)

[0034] Figure 7 Curve Extended-Range Trajectory at Different Rs

[0035] Figure 8 Schematic Diagram of Curve Extended-Range Trajectory in Mid-Guided Section DETAILED DESCRIPTION OF THE INVENTION

[0036] The present invention will be described in detail below in conjunction with the drawings and simulation examples.

[0037] A design method for curve extended-range trajectory in the mid-guided section, based on the missile position information output by inertial navigation in the mid-guided section, combined with real-time target information, and referring to the standard equation of a geometric circle, derives the calculation formula for the arc-shaped curve extended-range trajectory;

[0038] The design method for curve extended-range trajectory in the mid-guided section adopted by the present invention has a curve extended-range trajectory whose radian is only related to one parameter, and the parameter adjustment method is simple.

[0039] The trajectory radian can be adjusted according to the requirements of range extension and terminal velocity.

[0040] Figure 1 Schematic diagram of curve extended-range trajectory in the mid-guided section; wherein,

[0041] 1. hx0 and hy0 are the X-direction position and Y-direction position at the moment when missile altitude control starts;

[0042] 2. Xt and Yt are the X-direction position and Y-direction position of the target;

[0043] 3. DR0, DR1, a, and b are process variables in the formula derivation process;

[0044] 4. R is the curve range extension adjustment parameter.

[0045] The working process of the medium and long-range anti-tank missile can be described as follows: After the missile is launched, it makes full use of the engine working section to send the missile into a higher airspace, and then enters the mid-course guidance section. The missile adopts altitude control and flies along a certain trajectory before entering the terminal guidance section.

[0046] The process of determining the desired trajectory of the missile is as follows:

[0047] First, solve the line-of-sight angle η according to hy0 and Xt:

[0048] η = atan(hy0 / Xt)

[0049] In the mid-course guidance section, altitude control is adopted. hx0 and hy0 are the X and Y positions of the missile at the start time of altitude control; Xt and Yt are the X and Y positions of the target.

[0050] Then, solve the missile-to-target distance at the start time of altitude control:

[0051]

[0052] Solve DR1, a, and b:

[0053]

[0054]

[0055] Finally, give the desired trajectory of the missile in the mid-course guidance section in the form of an arc.

[0056]

[0057] DeH = DR2 + b

[0058] Where:

[0059] DeH is the solved desired trajectory of the missile;

[0060] X is the missile X-position information output by the inertial navigation during the missile flight;

[0061] R is the curve range extension adjustment parameter. In actual design, the value of R can be continuously adjusted to obtain a desired missile trajectory that meets the requirements.

[0062] The radian of the designed curve range extension trajectory is only related to one parameter, and the parameter adjustment method is simple.

[0063] The trajectory radian can be adjusted according to the range extension and terminal velocity requirements.

[0064] The initial value of R is taken as 0.5DR0. At this time, the solved ballistic trajectory is a standard semi-circular ballistic trajectory with the origin at the midpoint of the line connecting the missile and the target positions at the start of the mid-course guidance section, and the radius is 0.5DR0. According to actual requirements, the value of R can be adjusted. The larger R is, the larger the ballistic curvature is, and it gradually approaches the standard cloud circular ballistic trajectory; the smaller R is, the smaller the ballistic curvature is, and it gradually approaches the straight ballistic trajectory.

[0065] Taking a certain type of anti-tank missile as an example, the curve extended-range ballistic design method proposed in the present invention is simulated. Figure 1 and Figure 2 are the missile ballistic curves and flight speed curves when the straight ballistic trajectory and the curve extended-range ballistic trajectory are respectively adopted for a target at 40000m. The simulation results show that for a target at 40000m, the effects of the straight ballistic trajectory and the curve extended-range ballistic trajectory are similar, the terminal velocities of the missiles are basically the same, and both hit the target. Figures 3 to 6 are the simulation results of the straight ballistic trajectory and the curve extended-range ballistic trajectory for targets at 50000m and 55000m. The simulation results show that when facing a farther target, the missile cannot fly to and hit the target with the straight ballistic trajectory. In contrast, with the curve extended-range ballistic trajectory, the missile can hit the targets at 50000m and 55000m and still has a certain terminal velocity. Figure 7 are the curve extended-range ballistic trajectories for different values of R. It can be seen that the smaller the value of R is, the larger the expected ballistic curvature of the missile is, and the missile can also fly a farther distance.

Claims

1. A method for designing a curve extended-range ballistic trajectory in the mid-course guidance section, characterized in that, The method includes the following steps: Step 1: Obtain the inertial navigation output information; Step 2: Obtain the target information; Step 3: First, obtain the position at the starting moment of missile altitude control based on the information output by the inertial navigation, and at the same time obtain the position of the target according to the target information, and then determine the arc-shaped curve extended-range trajectory, that is, determine the expected trajectory DeH of the missile in the mid-course guidance section: DeH = DR2 + b; The specific solution of the parameters involved is as follows: Among them, hx0 and hy0 are the X-direction position and Y-direction position of the missile at the starting moment of altitude control; Xt and Yt are the X-direction position and Y-direction position of the target, and DR0 is the missile-target distance at the starting moment of altitude control; R is the curve extended-range adjustment parameter. Determine the value of R to obtain the expected trajectory of the missile.

2. A mid-course guidance section curve extended-range ballistic design method according to claim 1, characterized in that, Continuously adjust the value of R to obtain the expected trajectory of the missile that meets the requirements.

3. A method for designing a mid-course curved extended-range ballistic trajectory according to claim 1 or 2, characterized in that, The initial value of R is taken as 0.5DR0.

4. A mid-course curved range extension ballistic design method according to claim 1, characterized in that According to the initial value 0.5DR0 of R; increase or decrease the value of R to make the terminal velocity of the trajectory meet the requirements; this is the determined trajectory at this time.

Images