Method for correcting lateral shooting trajectory of cannonball

Abstract

The invention relates to a method for correcting a lateral shooting trajectory of a cannonball, and belongs to the technical field of airborne fire control. Comprising the following steps: acquiring a cannonball range, an aerial carrier altitude and pitch angle, a weapon azimuth angle, an aerial carrier vacuum speed, a true attack angle, a sideslip angle and a roll angle; calculating three components of system speed based on the vacuum speed, the true attack angle and the sideslip angle of the aerial carrier; calculating three components of horizontal system velocity based on the three components of aircraft system velocity, the pitch angle and the roll angle of the aerial carrier; calculating a horizontal component of an included angle between the shooting direction and the aerial carrier speed based on the horizontal system speed three-component and the weapon azimuth angle; respectively calculating a first correction and a second correction based on the horizontal component of the included angle between the shooting direction and the aerial carrier speed; calculating a correction coefficient based on the first correction amount and the second correction amount; and correcting the cannonball range by adopting the correction coefficient. The method is used for correcting the firing range of the shell when the attack angle of the muzzle is large during firing.

Description

Technical Field

[0001] The invention belongs to the technical field of airborne fire control, and in particular relates to a method for correcting the trajectory of a side-firing artillery shell. Background Art

[0002] Generally, the barrel of an onboard artillery is in the same direction as the machine axis, that is, the firing direction of the artillery is consistent with the direction of the aircraft speed. However, the firing direction of a rotating turret often deviates from the direction of the aircraft speed at a large angle, resulting in a large angle of attack at the moment of firing.

[0003] A projectile is generally a rigid body rotating at high speed. When it moves in the air, it is affected by aerodynamic forces and torques. If the angle of attack is small, the aerodynamic forces and torques can be considered as linear functions of the angle of attack. However, if the angle of attack is large, the flow of gas is a separated viscous flow, and the aerodynamic forces and torques show nonlinear laws. If a linear model is used to calculate the results, it will cause large errors.

[0004] The equations of nonlinear models and linear models are essentially different. Since the aircraft fire control mission computer has high real-time requirements for artillery trajectory calculation, it is unrealistic to run the nonlinear differential equations online to solve the trajectory. Therefore, a fast and simple method is needed to correct the trajectory according to the launch conditions. Summary of the invention

[0005] The technical problems to be solved by the present invention are:

[0006] In order to avoid the shortcomings of the prior art, the present invention provides a method for correcting the trajectory of a side-firing artillery shell, which is used to correct the range of the artillery shell when there is an angle between the muzzle firing direction and the carrier aircraft speed direction, that is, when the muzzle attack angle is large during firing.

[0007] In order to solve the above technical problems, the technical solution adopted by the present invention is:

[0008] A method for correcting the trajectory of a side-firing artillery shell, characterized by comprising:

[0009] The range of the shells is obtained through the fire control mission aircraft, the altitude and pitch angle of the carrier aircraft are obtained through the inertial navigation, the weapon azimuth is obtained through the gun servo mechanism, the true airspeed of the carrier aircraft is obtained through the pitot tube, and the true angle of attack, sideslip angle and roll angle are obtained through the angle of attack measurement device;

[0010] Computer system velocity three components based on true airspeed, true angle of attack and sideslip angle of the carrier aircraft;

[0011] Calculate the three components of horizontal system velocity based on the three components of aircraft system velocity, pitch angle and roll angle of the carrier aircraft;

[0012] Calculate the horizontal component of the angle between the firing direction and the carrier aircraft velocity based on the three components of the horizontal velocity and the weapon azimuth;

[0013] Calculate the first correction value and the second correction value based on the horizontal component of the angle between the shooting direction and the speed of the carrier aircraft;

[0014] calculating a correction coefficient based on the first correction amount and the second correction amount;

[0015] The range of the artillery shells is corrected using a correction factor.

[0016] A further technical solution of the present invention is as follows: the three components of the computer system speed based on the true airspeed, true angle of attack and sideslip angle of the carrier aircraft are as follows:

[0017] V0=Vcos(α)cos(β)

[0018] V1=-Vsin(α)cos(β)

[0019] V2=Vsin(β)

[0020] Among them, α is the true angle of attack, β is the sideslip angle, V is the true airspeed of the carrier aircraft, and V0, V1, and V2 are the three components of the aircraft system velocity.

[0021] A further technical solution of the present invention is to calculate the three components of the horizontal system velocity based on the three components of the aircraft system velocity, the pitch angle and the roll angle of the carrier aircraft, and the formula is as follows:

[0022] Vh0=V0cosθ-V1 cosγsinθ+V2 sinγsinθ

[0023] Vh1=V0 sinθ+V1 cosγcosθ-V2 sinγcosθ

[0024] Vh2=V1 sinγ+V2 cosγ

[0025] Among them, θ is the pitch angle of the carrier, γ is the roll angle, and Vh0, Vh1, and Vh2 are the three components of the horizontal system velocity.

[0026] A further technical solution of the present invention is to calculate the horizontal component of the angle between the firing direction and the carrier aircraft speed based on the three components of the horizontal system speed and the weapon azimuth, and the formula is as follows:

[0027]

[0028] in, is the weapon azimuth, It is the horizontal component of the angle between the shooting direction and the aircraft speed.

[0029] A further technical solution of the present invention is to calculate the first correction value based on the horizontal component of the angle between the shooting direction and the carrier speed, and the formula is as follows:

[0030]

[0031] A further technical solution of the present invention is to calculate the second correction value based on the horizontal component of the angle between the shooting direction and the carrier speed, and the formula is as follows:

[0032]

[0033] A further technical solution of the present invention is to calculate the correction coefficient based on the first correction amount and the second correction amount, and the formula is as follows:

[0034]

[0035] Where H is the altitude of the carrier aircraft and κ is the correction factor.

[0036] A further technical solution of the present invention is to use a correction coefficient to correct the range of the shell, and the formula is as follows:

[0037] A=κA'

[0038] Among them, A is the corrected range of the shell.

[0039] A computer system, characterized in that it comprises: one or more processors, and a computer-readable storage medium for storing one or more programs, wherein when the one or more programs are executed by the one or more processors, the one or more processors implement the above-mentioned method.

[0040] A computer-readable storage medium, characterized in that it stores computer-executable instructions, which are used to implement the above method when executed.

[0041] The beneficial effects of the present invention are:

[0042] The present invention provides a method for correcting the trajectory of a side-firing artillery shell, which can not only meet the accuracy of the correction but also ensure the limitation of the calculation time required by the fire control task machine. Compared with the prior art, it has the following advantages:

[0043] 1. It can improve the accuracy of range calculation: when the muzzle speed is inconsistent with the carrier aircraft speed at the time of firing, a large angle of attack will be formed. Under this condition, the nutation motion of the shell is greatly affected, thereby affecting the overall range of the shell. The present invention takes into account the influence of the angle on the range of the shell when the shell is fired at a large angle of attack on the basis of the range of the artillery itself, and combines experience and practical results to perform quantitative calculation, thereby improving the accuracy of range calculation of the shell.

[0044] 2. Ability to quickly realize on-board calculation: The calculation of the range of artillery shells is generally calculated by continuous integration of the model. This method takes too long to calculate and cannot meet the real-time requirements of airborne fire control. This method simplifies the calculation process and combines the actual shooting and simulation results to form a set of fast calculation methods, which can meet the fire control calculation time requirements. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] The drawings are only for the purpose of illustrating particular embodiments and are not to be considered limiting of the present invention. Like reference symbols denote like components throughout the drawings.

[0046] Figure 1 Flow chart of the method for correcting the trajectory of a side-firing artillery shell of the present invention. DETAILED DESCRIPTION

[0047] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0048] It should be noted that the terms "first", "second", etc. in the specification and claims of the present invention and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the terms used in this way can be interchangeable where appropriate, so that the embodiments of the present invention described herein can be implemented in an order other than those illustrated or described herein. In addition, the terms "including" and "having" and any variations thereof are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device that includes a series of steps or units is not necessarily limited to those steps or units that are clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0049] The present invention provides a method for calculating unmanned rotor cooperative illumination guidance points, such as Figure 1 As shown, the following steps are included:

[0050] Step 1: Information Acquisition

[0051] The aircraft fire control system obtains the shell range A' through the fire control mission aircraft, the aircraft altitude H and pitch angle θ through the inertial navigation, and the weapon azimuth through the gun servo mechanism. The true airspeed V of the carrier aircraft is obtained through the pitot tube, and the true angle of attack α, sideslip angle β and roll angle γ are obtained through the angle of attack measuring device.

[0052] Step 2: Calculate the horizontal component of the angle between the launch direction and the aircraft speed

[0053] Using formula (1) the three components of computer system speed V0, V1, V2

[0054]

[0055] α—true angle of attack, unit: °;

[0056] β—sideslip angle, unit: °;

[0057] V—aircraft true airspeed, in m / s;

[0058] Use formula (2) to calculate the three components of horizontal velocity Vh0, Vh1, Vh2

[0059]

[0060] θ—pitch angle, unit: °;

[0061] γ—roll angle, unit: °;

[0062] Use formula (3) to calculate the horizontal component of the angle between the launch direction and the carrier speed

[0063]

[0064] —weapon azimuth, in degrees;

[0065] Step 3: Calculate the correction amount p1

[0066] Calculate P1 using formula (4)

[0067]

[0068] —Horizontal component of the angle between the launch direction and the aircraft speed, unit: °;

[0069] Step 4: Calculate the correction amount p2

[0070] Calculate P2 using formula (5)

[0071]

[0072] —Horizontal component of the angle between the launch direction and the aircraft speed, unit: °;

[0073] Step 5: Calculate the range correction factor κ

[0074] Use formula (6) to calculate the correction factor κ

[0075]

[0076] H—aircraft height, in m;

[0077] Step 5: Calculate the corrected range A

[0078] Use formula (7) to calculate the corrected range A

[0079] A=κA'

[0080] Embodiment 1:

[0081] Step 1: Information Acquisition

[0082] The aircraft fire control system obtains the shell range A' through the fire control mission aircraft, the aircraft altitude H and pitch angle θ through the inertial navigation, and the weapon azimuth through the gun servo mechanism. The true airspeed V of the carrier aircraft is obtained through the pitot tube, and the true angle of attack α, sideslip angle β and roll angle γ are obtained through the angle of attack measuring device.

[0083] In this embodiment:

[0084] The aircraft fire control system obtains the artillery range of 3000 through the fire control mission aircraft, the aircraft altitude of 3500 and the pitch angle of -15° through the inertial navigation, the weapon azimuth of 70° through the artillery servo mechanism, the aircraft true airspeed of 250m / s through the pitot tube, and the true angle of attack of 3°, the sideslip angle of 2° and the roll angle of 10° through the angle of attack measurement device.

[0085] Step 2: Calculate the horizontal component of the angle between the launch direction and the aircraft speed

[0086] Using formula (1) the three components of computer system speed V0, V1, V2

[0087]

[0088] α—true angle of attack, unit: °;

[0089] β—sideslip angle, unit: °;

[0090] V—aircraft true airspeed, in m / s;

[0091] Use formula (2) to calculate the three components of horizontal velocity Vh0, Vh1, Vh2

[0092]

[0093] θ—pitch angle, unit: °;

[0094] γ—roll angle, unit: °;

[0095] Use formula (3) to calculate the horizontal component of the angle between the launch direction and the carrier speed

[0096]

[0097] —weapon azimuth, in degrees;

[0098] In this embodiment:

[0099] Use formula (1) to calculate V0, V1, V2

[0100] V0=250×cos(3×π / 180)×cos(2×π / 180)=249.505

[0101] V1=-250×sin(3×π / 180)×cos(2×π / 180)=-13.076

[0102] V2=250×sin(2×π / 180)=8.725

[0103] Use formula (2) to calculate Vh0, Vh1, Vh2

[0104] Vh0=249.505×cos(-15×π / 180)+13.076×cos(10×π / 180)×sin(-15×π / 180)+8.725×sin(10×π / 180)×sin(-15×π / 180)=237.278

[0105] Vh1=249.505×sin(-15×π / 180)-13.076×cos(10×π / 180)×cos(-15×π / 180)-8.725×sin(10×π / 180)×cos(-15×π / 180)=-78.479

[0106] Vh2=-13.076×sin(10×π / 180)+8.725×cos(10×π / 180)=6.322

[0107] Use formula (3) to calculate

[0108]

[0109] Step 3: Calculate the correction amount p1

[0110] Calculate P1 using formula (4)

[0111] p1=-9.268e-06×68.476 2-1.176e-04×|68.476|+1.001=0.949

[0112] Step 4: Calculate the correction amount p2

[0113] Calculate P2 using formula (5)

[0114] p2=-1.25e-05×68.476 2 -9.09e-05×|68.476|+1.001=0.936

[0115] Step 5: Calculate the range correction factor κ

[0116] Use formula (6) to calculate the correction factor κ

[0117]

[0118] H—aircraft height, in m;

[0119] Step 5: Calculate the corrected range A

[0120] Use formula (7) to calculate the corrected range A

[0121] A=0.945×3000=2835

[0122] The above description is only a specific implementation mode of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can easily think of various equivalent modifications or substitutions within the technical scope disclosed in the present invention, and these modifications or substitutions should be included in the protection scope of the present invention.

Claims

1. A method for correcting the trajectory of a side-firing artillery shell, characterized in that: include: The range of the shells is obtained through the fire control mission aircraft, the altitude and pitch angle of the carrier aircraft are obtained through the inertial navigation, the weapon azimuth is obtained through the gun servo mechanism, the true airspeed of the carrier aircraft is obtained through the pitot tube, and the true angle of attack, sideslip angle and roll angle are obtained through the angle of attack measurement device; Computer system velocity three components based on true airspeed, true angle of attack and sideslip angle of the carrier aircraft; Calculate the three components of horizontal system velocity based on the three components of aircraft system velocity, pitch angle and roll angle of the carrier aircraft; Calculate the horizontal component of the angle between the firing direction and the carrier aircraft velocity based on the three components of the horizontal velocity and the weapon azimuth; Calculate the first correction value and the second correction value based on the horizontal component of the angle between the shooting direction and the speed of the carrier aircraft; calculating a correction coefficient based on the first correction amount and the second correction amount; The range of the artillery shells is corrected using a correction factor.

2. A method for correcting the trajectory of a side-firing artillery shell according to claim 1, characterized in that: The three components of the computer system speed based on the true airspeed, true angle of attack and sideslip angle of the carrier aircraft are as follows: V0=Vcos(α)cos(β) V1=-Vsin(α)cos(β) V2=Vsin(β) Among them, α is the true angle of attack, β is the sideslip angle, V is the true airspeed of the carrier aircraft, and V0, V1, and V2 are the three components of the aircraft system velocity.

3. A method for correcting the trajectory of a side-firing artillery shell according to claim 2, characterized in that: The three components of the horizontal velocity are calculated based on the three components of the aircraft system velocity, the pitch angle and the roll angle of the carrier aircraft. The formula is as follows: Vh0=V0cosθ-V1 cosγsinθ+V2 sinγsinθ Vh1=V0 sinθ+V1 cosγcosθ-V2 sinγcosθ Vh2=V1 sinγ+V2 cosγ Among them, θ is the pitch angle of the carrier, γ is the roll angle, and Vh0, Vh1, and Vh2 are the three components of the horizontal system velocity.

4. A method for correcting the trajectory of a side-firing artillery shell according to claim 3, characterized in that: The horizontal component of the angle between the firing direction and the carrier aircraft velocity is calculated based on the three components of the horizontal velocity and the weapon azimuth. The formula is as follows: in, is the weapon azimuth, It is the horizontal component of the angle between the shooting direction and the aircraft speed.

5. A method for correcting the trajectory of a side-firing artillery shell according to claim 4, characterized in that: The first correction is calculated based on the horizontal component of the angle between the firing direction and the carrier speed. The formula is as follows:

6. A method for correcting the trajectory of a side-firing artillery shell according to claim 5, characterized in that: The second correction is calculated based on the horizontal component of the angle between the launch direction and the carrier speed. The formula is as follows:

7. A method for correcting the trajectory of a side-firing artillery shell according to claim 6, characterized in that: The correction coefficient is calculated based on the first correction amount and the second correction amount, and the formula is as follows: Where H is the altitude of the carrier aircraft and κ is the correction factor.

8. A method for correcting the trajectory of a side-firing artillery shell according to claim 7, characterized in that: The correction coefficient is used to correct the range of the artillery shells. The formula is as follows: A=κA' Among them, A is the corrected range of the shell.

9. A computer system, characterized in that include: One or more processors, and a computer-readable storage medium for storing one or more programs, wherein when the one or more programs are executed by the one or more processors, the one or more processors are enabled to implement the method of claim 1.

10. A computer-readable storage medium, characterized in that Computer executable instructions are stored, and when the instructions are executed, they are used to implement the method of claim 1.

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