Electromagnetic rail launcher electrical load simulation system

Abstract

The application discloses an electromagnetic track launcher electrical load simulation system, comprising: in series, a moving coil impedance model, a track inductance model, a track resistance model, a pivot track contact resistance model, an armature inductance model and an armature resistance model; the moving coil impedance model outputs the launching load displacement and the pivot track contact pressure based on the series loop current of the system; the moving coil impedance model also obtains the moving coil electromotive force based on the launching load speed, the series loop current and the track inductance gradient, and feeds back to the series loop of the simulation system; the track inductance model adjusts the series loop current of the simulation system based on the launching load displacement; the track resistance model obtains the track resistance voltage drop based on the launching load displacement and feeds back to the series loop of the simulation system; the pivot track contact resistance model obtains the contact resistance voltage drop between the track and the armature based on the pivot track contact pressure and feeds back to the series loop of the simulation system. The application can accurately simulate the dynamic coupling process of the electromagnetic track launcher.

Description

Technical Field

[0001] This invention relates to the field of electromagnetic launch modeling and simulation technology, specifically to an electrical load simulation system for an electromagnetic orbital launcher. Background Technology

[0002] Electromagnetic orbital launch technology utilizes the extremely high Ampere force generated when a pulsed high current flows through the track and armature as thrust, accelerating the armature and payload to several kilometers per second within milliseconds. It possesses unparalleled advantages over traditional launch methods that use gunpowder as the energy source, and has broad application prospects in military, aerospace, and scientific research fields. During electromagnetic orbital launch, as the armature and payload accelerate, the track length fed into the system circuit continuously increases. Simultaneously, the contact resistance and friction between the armature and track change complexly with the current magnitude and contact condition. The load impedance of the electromagnetic orbital launcher exhibits nonlinear changes, making it difficult to describe the electrical load characteristics of the launcher in detail through experimental testing.

[0003] Simulation calculation is an important and indispensable tool for studying the electromagnetic rail launch process. Currently, simulation calculation research both domestically and internationally covers almost all aspects of electromagnetic rail launch devices. For the electrical load of the electromagnetic rail launcher, the finite element method or a combination of finite element and boundary element methods are mainly used to obtain the static impedance value of the electromagnetic rail launcher through numerical simulation. However, the impedance change of the electromagnetic rail launcher caused by armature movement is not considered. Alternatively, the changing impedance value of the electromagnetic rail launcher is obtained by numerical simulation of lumped circuits based on assumed current waveforms, but the dynamic coupling process between current and electromagnetic rail launcher is not considered. Therefore, the simulation calculation results obtained by the above two methods have certain deviations from the actual situation. Summary of the Invention

[0004] In view of this, embodiments of the present invention provide an electromagnetic rail launcher electrical load simulation system to solve the problem that current electromagnetic rail launcher electrical load simulation methods fail to consider the dynamic changes of some parameters, resulting in discrepancies between simulation calculation results and actual conditions.

[0005] This invention provides an electrical load simulation system for an electromagnetic track launcher, comprising: a motional impedance model, a track inductance model, a track resistance model, a pivot-rail contact resistance model, an armature inductance model, and an armature resistance model connected in series.

[0006] The motional impedance model outputs the launch load displacement and pivot rail contact pressure based on the series loop current of the simulation system; the motional impedance model also obtains the motional electromotive force based on the calculated launch load velocity, the series loop current and the track inductance gradient, and feeds it back to the series loop of the simulation system.

[0007] The track inductance model adjusts the series loop current of the simulation system based on the displacement of the launch load.

[0008] The orbital resistance model obtains the orbital resistance voltage drop based on the launch load displacement and feeds it back to the series circuit of the simulation system.

[0009] The armature-rail contact resistance model is based on the armature-rail contact pressure, obtains the contact resistance voltage drop between the armature and the rail, and feeds it back to the series circuit of the simulation system.

[0010] In some optional embodiments, the dynamic impedance model determines the electromagnetic thrust based on the series loop current and the track inductance gradient; and / or determines the frictional force between the armature and the payload based on the electromagnetic thrust and the track spacing, armature tail fin length, armature tail fin tilt angle, armature interference preload pressure, payload frictional force, and dynamic friction coefficient; and / or determines the launch payload acceleration, launch payload velocity, and launch payload displacement based on the electromagnetic thrust, the frictional force between the armature and the payload, and the launch payload mass.

[0011] In some optional implementations, the motional impedance model includes a first controlled voltage source and a first arithmetic unit. The first arithmetic unit is used to acquire the motional electromotive force and input it into the controlled terminal of the first controlled voltage source so as to feed the motional electromotive force back to the series circuit of the simulation system.

[0012] In some optional embodiments, the electromagnetic thrust F is calculated using the following formula:

[0013] F = L'I 2 / 2, where L' is the track inductance gradient and I is the series loop current;

[0014] The frictional force f between the armature and the payload is calculated using the following formula:

[0015] Where μ1 is the coefficient of kinetic friction, F C0 d1 is the armature interference preload pressure, d1 is the armature tail fin length, X is the track spacing, θ is the armature tail fin tilt angle, and 2f2 is the effective load friction force.

[0016] The launch load acceleration 'a' is calculated using the following formula:

[0017] a = (Ff) / m, where m is the mass of the launch payload;

[0018] The launch payload velocity v is calculated using the following formula:

[0019] v = ∫adt, where t is time;

[0020] The launch load displacement s is calculated using the following formula:

[0021] s=∫vdt.

[0022] In some optional embodiments, the track inductance model includes a controlled current source and a second computing unit; the input terminal of the controlled current source is connected to the output terminal of the track inductance model as the input terminal of the track inductance model, and the output terminal of the controlled current source is connected to the input terminal of the track resistance model as the output terminal of the track inductance model.

[0023] The second arithmetic unit obtains the inductor current based on the launch load displacement, the track inductance gradient, the track initial inductance, and the terminal voltage of the controlled current source, and inputs the inductor current into the controlled terminal of the controlled current source.

[0024] In some optional embodiments, the inductor current I is calculated using the following formula:

[0025]

[0026] Where u2 is the terminal voltage of the controlled current source, L0 is the initial inductance of the track, L' is the inductance gradient of the track, s is the displacement of the launch load, and t is time.

[0027] In some optional embodiments, the track resistance model includes a third computing unit and a second controlled voltage source. The third computing unit obtains the track resistance voltage drop based on the launch load displacement, track resistance gradient, track initial resistance, and the series loop current, and inputs the track resistance voltage drop into the controlled terminal of the second controlled voltage source to feed the track resistance voltage drop back to the series loop of the simulation system.

[0028] In some optional embodiments, the track resistance voltage drop u3 is calculated using the following formula:

[0029] u3=(R0+R's)I

[0030] Wherein, R0 is the initial resistance of the track, R' is the track resistance gradient, s is the launch load displacement, and I is the series loop current.

[0031] In some optional embodiments, the pivot-rail contact resistance model includes a fourth computational unit and a third controlled voltage source. The fourth computational unit obtains the contact resistance voltage drop between the armature and the rail based on the pivot-rail contact pressure, the series circuit current, the armature stiffness, the pivot-rail contact area, the rail resistivity, and the armature resistivity. The contact resistance voltage drop between the armature and the rail is input to the third controlled voltage source to feed back the contact resistance voltage drop between the armature and the rail to the series circuit of the simulation system.

[0032] In some optional embodiments, the contact resistance voltage drop u4 between the armature and the rail is calculated using the following formula:

[0033]

[0034] Where, ρ rail Let ρ be the orbital resistivity. arm Let A be the armature resistivity, c be the first preset coefficient, and A be the armature resistivity. c H represents the contact area of ​​the pivot rail. soft F represents the armature hardness. c The pivot rail contact pressure is n, the second preset system is I, and the series circuit current is I.

[0035] This invention provides an electrical load simulation system for an electromagnetic rail launcher, comprising a motional impedance model, a track inductance model, a track resistance model, a pivot-rail contact resistance model, an armature inductance model, and an armature resistance model. These models are connected in series to form the electromagnetic rail launcher electrical load simulation system. The motional impedance model outputs launch load displacement and pivot-rail contact pressure parameters, which serve as inputs to the track inductance model, track resistance model, and pivot-rail contact resistance model. This electromagnetic rail launcher electrical load simulation system couples motion, friction, and structural parameters with circuit parameters, enabling more realistic dynamic simulations. It provides accurate and reliable simulations for studying the changes in various parameters during electromagnetic rail launch and the energy transmission and conversion process. Attached Figure Description

[0036] The features and advantages of the invention will be more clearly understood by referring to the accompanying drawings, which are schematic and should not be construed as limiting the invention in any way. In the drawings:

[0037] Figure 1 A schematic diagram of the overall structure of an electromagnetic rail launcher electrical load simulation system provided in an embodiment of the present invention;

[0038] Figure 2 This is a schematic diagram of the structure of a motional impedance model provided in an embodiment of the present invention;

[0039] Figure 3This is a schematic diagram of the structure of a track inductor model provided in an embodiment of the present invention;

[0040] Figure 4 This is a schematic diagram of the structure of a track resistance model provided in an embodiment of the present invention;

[0041] Figure 5 This is a schematic diagram of a pivot contact resistance model provided in an embodiment of the present invention. Detailed Implementation

[0042] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0043] It should be noted that the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Unless otherwise specified, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element. Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. In the following descriptions of embodiments, "a plurality of" means two or more, unless otherwise expressly specified.

[0044] Please see Figure 1 The present invention provides an electrical load simulation system for an electromagnetic track launcher, comprising: a dynamic impedance model, a track inductance model, a track resistance model, a pivot-rail contact resistance model, an armature inductance model, and an armature resistance model connected in series.

[0045] The motional impedance model outputs the launch load displacement s and the armature contact pressure Fc based on the series loop current of the simulation system. The model also obtains the motional electromotive force (EMF) based on the calculated launch load velocity, the series loop current, and the track inductance gradient, and feeds it back into the series loop of the simulation system. The series loop current is acquired in real time. The launch load and armature move synchronously, therefore the armature displacement equals the launch load displacement. The motional EMF u1 is calculated using the following formula: u1 = L'Iv, where L' is the track inductance gradient, I is the series loop current, and v is the launch load velocity. The motional EMF fed back into the series loop of the simulation system can affect the waveform of the series loop current.

[0046] The track inductance model adjusts the series loop current of the simulation system based on the displacement of the launch load.

[0047] The orbital resistance model obtains the orbital resistance voltage drop based on the launch load displacement and feeds it back to the series circuit of the simulation system.

[0048] The armature-rail contact resistance model is based on the armature-rail contact pressure, obtains the contact resistance voltage drop between the armature and the rail, and feeds it back to the series circuit of the simulation system.

[0049] During electromagnetic rail launch, the Ampere force generated by the current drives the armature and payload to move. This causes a change in the impedance of the electromagnetic rail launcher, which consists of the track and armature, and this change alters the current waveform, ultimately affecting physical quantities such as the speed of the armature and payload. To address this phenomenon, this invention provides an electromagnetic rail launcher electrical load simulation system, including a motional impedance model, a track inductance model, a track resistance model, a armature-rail contact resistance model, an armature inductance model, and an armature resistance model. These models are connected in series to form the electromagnetic rail launcher electrical load simulation system. The motional impedance model outputs the launch payload displacement and armature-rail contact pressure parameters, which serve as inputs to the track inductance model, track resistance model, and armature-rail contact resistance model. This electromagnetic rail launcher electrical load simulation system couples motion, friction, and structural parameters with circuit parameters, enabling more realistic dynamic simulations. It provides accurate and reliable simulations for studying the changes in various parameters during electromagnetic rail launch and the energy transmission and conversion process.

[0050] In some specific implementations, the motional impedance model determines the electromagnetic thrust based on the series loop current and the track inductance gradient; and / or determines the frictional force between the armature and the payload based on the electromagnetic thrust and the track spacing, armature tail fin length, armature tail fin tilt angle, armature interference preload pressure, payload frictional force, and dynamic friction coefficient, wherein the frictional force refers to dynamic frictional force; and / or determines the launch payload acceleration, launch payload velocity, and launch payload displacement based on the electromagnetic thrust, the frictional force between the armature and the payload, and the launch payload mass (the sum of the armature and payload masses).

[0051] For some specific implementation methods, please refer to Figure 2 The motional impedance model includes a first controlled voltage source and a first computational unit. The first computational unit is used to acquire the motional electromotive force (EMF) and input it to the controlled terminal of the first controlled voltage source to feed the EMF back to the series circuit of the simulation system. The electromagnetic thrust, the frictional force of the armature and the payload, the acceleration of the launch payload, the velocity of the launch payload, and the displacement of the launch payload are also calculated by the first computational unit. The motional impedance model also includes a current sampling unit for acquiring the series circuit current required for calculation. Specifically, the input of the first controlled voltage source is used as the input of the motional impedance model, and the output of the first controlled voltage source is used as the output of the motional impedance model, which is connected to the input of the track inductance model. The current sampling unit can be set at the input terminal of the first controlled voltage source.

[0052] In some specific implementations, the electromagnetic thrust F is calculated using the following formula:

[0053] F = L'I 2 / 2, where L' is the track inductance gradient and I is the series loop current;

[0054] The frictional force f between the armature and the payload is calculated using the following formula:

[0055] Where μ1 is the coefficient of kinetic friction, F C0 d1 is the armature interference preload pressure, d1 is the armature tail fin length, X is the track spacing, θ is the armature tail fin tilt angle, 2f2 is the effective load friction force, f2 is the effective load unilateral friction force, and f1 is the armature unilateral friction force.

[0056] The net force on the launching payload, i.e., the net force on the armature in the direction of motion, is: F A =Ff;

[0057] The launch load acceleration 'a' is calculated using the following formula:

[0058] Where m is the mass of the launch payload;

[0059] The launch payload velocity v is calculated using the following formula:

[0060] v = ∫adt, where t is time;

[0061] The launch load displacement s is calculated using the following formula:

[0062] s=∫vdt.

[0063] The pivot rail contact pressure Fc is calculated using the following formula:

[0064]

[0065] For some specific implementation methods, please refer to Figure 3 The track inductance model includes a controlled current source and a second computing unit; the input terminal of the controlled current source is connected to the output terminal of the track inductance model as the input terminal of the track inductance model, and the output terminal of the controlled current source is connected to the input terminal of the track resistance model as the output terminal of the track inductance model.

[0066] The second computing unit obtains the inductor current based on the launch load displacement, the track inductance gradient, the track initial inductance, and the terminal voltage of the controlled current source, and inputs the inductor current into the controlled terminal of the controlled current source to feed the inductor current back to the series circuit of the simulation system.

[0067] Specifically, the inductor current I is calculated using the following formula:

[0068]

[0069] Where u2 is the terminal voltage of the controlled current source, L0 is the initial inductance of the track, L' is the gradient of the track inductance, s is the displacement of the launch payload, t is time, and L0+L's is the current total track inductance.

[0070] For some specific implementation methods, please refer to Figure 4The track resistance model includes a third computational unit and a second controlled voltage source. The third computational unit obtains the track resistance voltage drop based on the launch load displacement, track resistance gradient, initial track resistance, and series loop current. This track resistance voltage drop is input to the controlled terminal of the second controlled voltage source to feed it back to the series loop of the simulation system. The track resistance model may also include a current sampling unit, which is also used to collect the series loop current required for calculation. Similar to the motional impedance model, the input of the second controlled voltage source of the track resistance model is connected to the output terminal of the track inductance model, and the output of the second controlled voltage source is connected to the input terminal of the pivot contact resistance model. The current sampling unit can be located at the input terminal of the second controlled voltage source.

[0071] In some specific implementations, the track resistance voltage drop u3 is calculated using the following formula:

[0072] u3=(R0+R's)I

[0073] Wherein, R0 is the initial resistance of the track, R' is the track resistance gradient, s is the launch load displacement, and I is the series loop current.

[0074] For some specific implementation methods, please refer to Figure 5 The pivot-rail contact resistance model includes a fourth computational unit and a third controlled voltage source. The fourth computational unit, based on the pivot-rail contact pressure, the series circuit current, the armature stiffness, the pivot-rail contact area (i.e., the contact area between the armature and the rail), the rail resistivity, and the armature resistivity, obtains the contact resistance voltage drop between the armature and the rail. This voltage drop is then input to the third controlled voltage source to feed back the contact resistance voltage drop between the armature and the rail to the series circuit of the simulation system. The series circuit current is acquired in real-time by the pivot-rail contact resistance model. The pivot-rail contact area is obtained by multiplying the rail height (y) and the armature tail fin length (d1).

[0075] Specifically, the pivot-rail contact resistance model can also include a current sampling unit, which is also used to collect the series loop current required for calculation. Similar to the motional impedance model and the rail resistance model, the input of the third controlled voltage source of the pivot-rail contact resistance model is connected to the output of the rail resistance model as the input of the pivot-rail contact resistance model, and the output of the third controlled voltage source is connected to the input of the armature inductance model as the output of the pivot-rail contact resistance model. The current sampling unit can be set at the input terminal of the third controlled voltage source.

[0076] In some specific implementations, the contact resistance voltage drop u4 between the armature and the track is calculated using the following formula:

[0077]

[0078] Where, ρ rail Let ρ be the orbital resistivity (OPCu). arm Let A be the armature resistivity (OAI), c be a first preset coefficient, and A be the armature resistivity (OAI). c H represents the contact area of ​​the pivot rail. soft F represents the armature hardness. c Let n be the pivot rail contact pressure, c be the second preset system, and I be the series circuit current. Wherein, n can be 0.63, and c can be 10.4 × 10⁻⁶. -4 .

[0079] The various embodiments in this specification are described in a progressive manner. The same or similar parts between the various embodiments can be referred to each other. Each embodiment focuses on describing the differences from other embodiments.

[0080] The above description is merely an embodiment of this application and is not intended to limit this application. Various modifications and variations can be made to this application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principle of this application should be included within the scope of the claims of this application.

Claims

1. An electrical load simulation system for an electromagnetic orbital launcher, characterized in that, include: The motional impedance model, track inductance model, track resistance model, armature contact resistance model, armature inductance model, and armature resistance model are connected in series. The motional impedance model outputs the launch load displacement and pivot rail contact pressure based on the series loop current of the simulation system; the motional impedance model also obtains the motional electromotive force based on the calculated launch load velocity, the series loop current and the track inductance gradient, and feeds it back to the series loop of the simulation system. The track inductance model adjusts the series loop current of the simulation system based on the displacement of the launch load. The orbital resistance model obtains the orbital resistance voltage drop based on the launch load displacement and feeds it back to the series circuit of the simulation system. The pivot-rail contact resistance model is based on the pivot-rail contact pressure, obtains the contact resistance voltage drop between the rail and the armature, and feeds it back to the series circuit of the simulation system.

2. The simulation system according to claim 1, characterized in that, The dynamic impedance model determines the electromagnetic thrust based on the series loop current and the track inductance gradient; and / or determines the frictional force between the armature and the payload based on the electromagnetic thrust and the track spacing, armature tail fin length, armature tail fin tilt angle, armature interference preload pressure, payload frictional force, and dynamic friction coefficient; and / or determines the launch payload acceleration, launch payload velocity, and launch payload displacement based on the electromagnetic thrust, the frictional force between the armature and the payload, and the launch payload mass.

3. The simulation system according to claim 1 or 2, characterized in that, The motional impedance model includes a first controlled voltage source and a first arithmetic unit. The first arithmetic unit is used to acquire the motional electromotive force and input it into the controlled terminal of the first controlled voltage source so as to feed the motional electromotive force back to the series circuit of the simulation system.

4. The simulation system according to claim 2, characterized in that, The electromagnetic thrust F is calculated using the following formula: F = L'I 2 2, where L' is the track inductance gradient and I is the series loop current; The frictional force f between the armature and the payload is calculated using the following formula: Where μ1 is the coefficient of kinetic friction, F C0 d1 is the armature interference preload pressure, d1 is the armature tail fin length, X is the track spacing, θ is the armature tail fin tilt angle, and 2f2 is the effective load friction force. The launch load acceleration 'a' is calculated using the following formula: a = (Ff)m, where m is the mass of the launch payload; The launch payload velocity v is calculated using the following formula: v = ∫adt, where t is time; The launch load displacement s is calculated using the following formula: s=∫vdt.

5. The simulation system according to claim 1, characterized in that, The track inductance model includes a controlled current source and a second computing unit; the input terminal of the controlled current source is connected to the output terminal of the track inductance model as the input terminal of the track inductance model, and the output terminal of the controlled current source is connected to the input terminal of the track resistance model as the output terminal of the track inductance model. The second arithmetic unit obtains the inductor current based on the launch load displacement, the track inductance gradient, the track initial inductance, and the terminal voltage of the controlled current source, and inputs the inductor current into the controlled terminal of the controlled current source.

6. The simulation system according to claim 5, characterized in that, The inductor current I is calculated using the following formula: Where u2 is the terminal voltage of the controlled current source, L0 is the initial inductance of the track, L' is the inductance gradient of the track, s is the displacement of the launch load, and t is time.

7. The simulation system according to claim 1, characterized in that, The track resistance model includes a third computing unit and a second controlled voltage source. The third computing unit obtains the track resistance voltage drop based on the launch load displacement, track resistance gradient, track initial resistance, and series loop current, and inputs the track resistance voltage drop into the controlled terminal of the second controlled voltage source to feed the track resistance voltage drop back to the series loop of the simulation system.

8. The simulation system according to claim 7, characterized in that, The track resistance voltage drop u3 is calculated using the following formula: u3=(R0+R's)I Wherein, R0 is the initial resistance of the track, R' is the track resistance gradient, s is the launch load displacement, and I is the series loop current.

9. The simulation system according to claim 1, characterized in that, The pivot-rail contact resistance model includes a fourth computing unit and a third controlled voltage source. The fourth computing unit obtains the contact resistance voltage drop between the armature and the rail based on the pivot-rail contact pressure, the series circuit current, the armature stiffness, the pivot-rail contact area, the rail resistivity, and the armature resistivity. The contact resistance voltage drop between the armature and the rail is input to the third controlled voltage source to feed back the contact resistance voltage drop between the armature and the rail to the series circuit of the simulation system.

10. The simulation system according to claim 9, characterized in that, The contact resistance voltage drop u4 between the armature and the track is calculated using the following formula: Where, ρ rail Let ρ be the orbital resistivity. arm Let A be the armature resistivity, c be the first preset coefficient, and A be the armature resistivity. c H represents the contact area of ​​the pivot rail. soft F represents the armature hardness. c The pivot rail contact pressure is n, the second preset system is I, and the series circuit current is I.

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