A method for interceptor deployment and deorbiting decision in a space-based anti-missile scenario

Abstract

This invention discloses a method for interceptor deployment and deorbiting decision-making in a space-based anti-missile scenario. It includes modeling the time interception window, establishing a model of the time window during the interception process; establishing a model of the space interception window, obtaining a space interception window model for the opposing ballistic missile; and calculating and analyzing the single-orbit distribution density of on-orbit interceptors. This enables the space-based interceptor weapon system to allocate the optimal number of on-orbit interceptors to intercept the opposing missile under different interception requirements. This invention provides a reference for solving the interceptor deployment and corresponding weapon deorbiting decisions in space-based anti-missile systems, enhancing the rationality and accuracy of space-based anti-missile interception systems, and has excellent application prospects in the aerospace field.

Description

Technical Field

[0001] This invention belongs to the field of anti-missile technology, specifically relating to a method for interceptor deployment and deorbiting decision-making in a space-based anti-missile scenario. Background Technology

[0002] Space-based missile defense primarily targets high-speed trans-domain vehicles (TSVs), which are powerful and difficult to intercept. With their strong penetration capabilities, high accuracy, and ability to carry nuclear and biological warheads, TSVs are among the most threatening offensive weapons in modern warfare. TSVs are powered by rocket engines in their initial flight phase; after engine shutdown, they follow a free-fall trajectory combined with glide. Therefore, their trajectory is relatively predictable, typically consisting of a boost phase, a glide phase, and a terminal guidance phase. Missile defense interception can be divided into two phases: boost-phase interception and glide-phase interception. Each phase presents its own difficulties and challenges, making missile defense interception a highly complex technology.

[0003] In the process of anti-missile interception, the interception strategy of space-based weapon systems against high-speed cross-domain vehicles launched by the Blue Force is usually based on principles such as early warning, target identification, rapid response and multi-layered defense, and is usually part of the overall defense system to ensure effective interception and defense against enemy missiles.

[0004] Furthermore, in the interception strategy of space-based weapon systems, the distribution of interceptor deployment and the corresponding weapon deorbiting decisions are crucial. Therefore, it is urgent to study a method for interceptor deployment and deorbiting decisions in space-based missile defense. Summary of the Invention

[0005] To overcome the shortcomings of existing technologies, this invention provides a method for interceptor deployment and deorbiting decisions in space-based missile defense scenarios. This method includes modeling the time interception window, establishing a model of the time window during the interception process; establishing a model of the space interception window, obtaining a space interception window model for the opposing ballistic missile; and calculating and analyzing the single-track distribution density of on-orbit interceptors, enabling the space-based interceptor weapon system to allocate the optimal number of on-orbit interceptors to intercept the opposing missile under different interception requirements. This invention provides valuable insights for solving the problems of interceptor deployment and corresponding weapon deorbiting decisions in space-based missile defense, enhancing the rationality and accuracy of space-based missile defense interception systems, and has excellent application prospects in the aerospace field.

[0006] The technical solution adopted by this invention to solve its technical problem is as follows:

[0007] Step 1: Build the time interception window model;

[0008] Step 1-1: For the Blue Force missile, the glide phase flight trajectory is determined by its active phase shutdown point parameters (r).k ,v k ,θ k It is determined that its flight trajectory is approximately an elliptical trajectory; according to elliptic theory, the relevant parameters of an elliptical trajectory are: semi-major axis a, semi-minor axis b, eccentricity e, and semi-aperture P, which are calculated using the following formula:

[0009]

[0010] In the formula, r0 is the geocentric distance from the point of shutdown in the active phase, v0 is the velocity at the point of shutdown in the active phase, θ0 is the trajectory inclination angle at the point of shutdown in the active phase; γ0 is called the energy parameter, and μ is the Earth's gravitational coefficient; where:

[0011]

[0012] Steps 1-2: Let the time taken for the ballistic missile to travel from its perigee p to the activation point k0, the earliest interception point k1, and the latest interception point k2 be respectively... The approximation angles of the ballistic missile as it flies from perigee p to the activation point k0, the earliest intercept point k1, and the latest intercept point k2 are E0, E1, and E2, respectively. According to Kepler's equations:

[0013]

[0014] Then we get:

[0015]

[0016] In the formula, n represents the average motion per unit time, E represents the asymmetry angle, and e represents the eccentricity of the orbit.

[0017] Steps 1-3: From equation (4), derive the time it takes for the Blue Force missile to travel from the active phase shutdown point k0 to the earliest interception point k1. Time to reach the latest intercept point K2 They are respectively:

[0018]

[0019] In the formula, E0, E1, and E2 are the approach angles corresponding to the target ballistic active phase shutdown point k0, the earliest interception point k1, and the latest interception point k2, respectively, and their calculation formulas are as follows:

[0020]

[0021] Where r1 and r2 represent the distance between the centers of the earth at the earliest interception point k1 and the latest interception point k2, respectively; v1 and v2 represent the velocities at the earliest interception point k1 and the latest interception point k2, respectively.

[0022] At this point, the time window for obtaining information about the Red Force's missile interception is...

[0023] t w =[t0,t1] (7)

[0024] in:

[0025]

[0026] Step 2: Set up a space interception window;

[0027] Step 2-1: Let the earliest collision point in the active phase be κ1, the latest collision point be κ2, and the altitude at point κ1 be defined as h1. Let the blue team's missile travel time be t. 1b The Red Force missile's flight time is t. 1r At point κ2, the altitude is h2, and the blue team's missile flight time is t. 2b The Red Force missile's flight time is t. 2r ;

[0028] Let the earliest collision point during the glide phase be κ3, the latest collision point be κ4, and the altitude at point κ3 be defined as h3. Let the blue force missile's flight time be t. 3b The Red Force missile's flight time is t. 3r At point κ4, the altitude is h4, and the Blue Force missile's flight time is t. 4b The Red Force missile's flight time is t. 4r ;

[0029] Then point κ2 is the separation point of the Blue Force missile during the active phase, and the Blue Force missile's operating time at the separation point during the active phase is t. 2b At an altitude of h2, the Blue Force missile has traveled a distance x along the x-axis of the launch system. 2b ;

[0030] Step 2-2: Assume the anti-missile interceptor weapon re-enters orbit at an angle of attack α after deorbiting. At an altitude of h2, what is the red force missile's orbital time t? 2r From the red force's altitude-range curve, we know that the red force's missile has traveled a distance x along the x-axis of the launch system at this time. 2r ;

[0031] At this point, the time difference between the red and blue teams is t. △ :

[0032] t △ =t 2b -t 2r (9)

[0033] That is, the on-orbit motion time of the interceptor weapon is t. △ The formula for calculating the forward distance of the on-orbit motion at this time is:

[0034] △x 2r =v g ×t △(10)

[0035] The distance between the red and blue teams is x2:

[0036] x2=x 2b +x 2r +△x 2r (11)

[0037] Suppose that when the angle of attack is α, at t 2r At any given moment, the altitude h of the interceptor weapon. 2r Equivalent to the ideal interception point altitude h2, we obtain x 2r x 2b x2;t 1r The time of the earliest collision point κ1 is used to obtain x. 2r x 2b x1;

[0038] In summary, the active segment interception window x z :

[0039] x z =[x1,x2] (12)

[0040] Based on the interceptor weapon capability specifications, the size of the lateral window during the active phase is tentatively set to x. zc0 After continuous iteration, the size of the lateral window during the active phase of the interceptor weapon was determined to be x. zc ;

[0041] Steps 2-3: Theoretically, the earliest collision point κ3 of the gliding phase interception coincides with the latest collision point κ2 of the active phase interception, thus obtaining x. 3r x 4b At this point, the distance between the red and blue sides at the earliest collision point κ3 during the gliding phase is x3:

[0042] x3=x 3r +x 3b (13)

[0043] Knowing κ4, t 4r x at time 4r x 4b At this point, the distance between the red and blue sides at the latest collision point κ4 during the gliding phase is x4:

[0044] x4=x 4r +x 4b (14)

[0045] Therefore, the glide segment interception window x is obtained. h :

[0046] x h = [x3, x4] (15)

[0047] Based on the interceptor weapon capability specifications, the size of the lateral window during the active phase is first set as follows: Through continuous iteration, the size of the lateral window during the active phase of the interceptor weapon was determined to be x. hc ;

[0048] Step 3: Update the interceptor deployment;

[0049] The total window span difference for interception is △x:

[0050] △x=x4-x1 (16)

[0051] The longitude spanned along the equator is △l:

[0052] △l=△x / l0 (17)

[0053] Where l0 is the distance per unit longitude at the equator;

[0054] Assuming a window contains at least n missiles, the number N of on-orbit interceptors distributed in a single orbit is obtained as follows:

[0055] N=(360 / △l)×n (18)

[0056] Step 4: Optimize interceptor deployment;

[0057] When there is no interceptor in the current interception window, the active segment window is as follows:

[0058] x z =[x1,x2] (19)

[0059] The gliding window at this time is:

[0060] x h =[x3,x4] (20)

[0061] Let the optimization variable be x. o The optimized active and gliding segment windows are as follows:

[0062]

[0063] At this point, the total window span difference for interception is △x':

[0064] △x'=x4-x1+2x o (twenty two)

[0065] The longitude spanned along the equator is △l':

[0066] △l'=△x' / l0 (23)

[0067] Assuming a window contains at least n missiles, the number of on-orbit interceptors distributed in a single orbit is obtained as N':

[0068] N'=(360 / △l')×n (24)

[0069] Step 5: Derailment decision;

[0070] Step 5-1: There are M interceptors, namely interceptors L1, L2...L... M All of them are within the temporal and spatial interception windows, and the relative distances between each interceptor and the target are obtained as R1, R2...R M ;

[0071] Step 5-2: Sort the deorbit priorities of each interceptor, and sort them according to the principle of relative distance between the interceptor and the target from smallest to largest.

[0072] Step 5-3: Set interceptors L1, L2...L M The relationship between the relative distances to the target is as follows:

[0073] R1 <R2<…<R M (25)

[0074] The selection of interceptors is based on the interception scenario. Assuming T interceptors are needed to intercept the target, the interceptors requiring deorbiting and reentry interception are L1, ..., L2. T .

[0075] Preferably, T ≥ 1.

[0076] The beneficial effects of this invention are as follows:

[0077] This invention addresses the deployment and deorbiting decision-making of interceptors in space-based anti-missile scenarios. This method enables the rational distribution of space-based anti-missile interceptors and the allocation of the optimal friendly interceptors for interception when enemy missiles attack, avoiding resource waste caused by unreasonable distribution of space-based interceptors and improving the completeness of the space-based anti-missile system. Attached Figure Description

[0078] Figure 1 This is a schematic diagram of the overall process provided by the present invention.

[0079] Figure 2 This is a graph showing the change in the height of the blue square over time according to an embodiment of the present invention.

[0080] Figure 3 This is a graph showing the change of the blue side's range over time in an embodiment of the present invention.

[0081] Figure 4 This is a graph showing the change in the height of the blue square as a function of the firing range in an embodiment of the present invention.

[0082] Figure 5 This is a graph showing the change of the red square height over time in an embodiment of the present invention.

[0083] Figure 6 This is a graph showing the change in the height of the red side with the range in an embodiment of the present invention.

[0084] Figure 7 This is a graph showing the change in the height of the red and blue sides over time according to an embodiment of the present invention.

[0085] Figure 8 This is a graph showing the change of the red team's range over time at the moment of interception in an embodiment of the present invention.

[0086] Figure 9 This is a graph showing the change of the blue team's range over time at the moment of interception in an embodiment of the present invention. Detailed Implementation

[0087] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0088] like Figure 1 As shown, a method for deploying and deorbiting interceptors in a space-based anti-missile system mainly includes the following steps:

[0089] Step 1: Build the time interception window model;

[0090] The time interception window model is represented as:

[0091] For the Blue Force missile, the glide phase flight trajectory and its active phase shutdown point parameters (r) k ,v k ,θ k Therefore, its flight trajectory can be approximated as an elliptical trajectory. From elliptic theory, the relevant parameters of an elliptical trajectory are: semi-major axis *a*, semi-minor axis *b*, eccentricity *e*, and semi-aperture *P*. The calculation formula can be expressed as:

[0092]

[0093] In the formula, r0 is the geocentric distance from the point of shutdown in the active phase, v0 is the velocity at the point of shutdown in the active phase, θ0 is the trajectory inclination angle at the point of shutdown in the active phase; γ0 is called the energy parameter, and μ is the Earth's gravitational coefficient. Where:

[0094]

[0095] Assume the time taken for the ballistic missile to travel from its perigee p to the activation point k0, the earliest intercept point k1, and the latest intercept point k2 are respectively... The approximation angles of the ballistic missile as it flies from perigee p to the activation point k0, the earliest intercept point k1, and the latest intercept point k2 are E0, E1, and E2, respectively. According to Kepler's equations:

[0096]

[0097] Then we can obtain:

[0098]

[0099] From the above formula, we can deduce the time it takes for the Blue Force missile to travel from the active phase shutdown point k0 to the earliest interception point k1. Time to reach the latest intercept point K2 They are respectively:

[0100]

[0101] In the formula, E0, E1, and E2 are the approach angles corresponding to the target's ballistic activation point k0, the earliest interception point k1, and the latest interception point k2, respectively. The calculation formula is as follows:

[0102]

[0103] At this point, the time window for obtaining information about the Red Force's missile interception is...

[0104] t w =[t0,t1] (32)

[0105] in:

[0106]

[0107] Step 2: Set up a space interception window;

[0108] Considering that the earliest collision point in the active phase is κ1 and the latest collision point is κ2, and the altitude of point κ1 is defined as h1, the blue force missile's flight time is t. 1b The Red Force missile's flight time is t. 1r At point κ2, the altitude is h2, and the blue team's missile flight time is t. 2b The Red Force missile's flight time is t. 2r .

[0109] Considering that the earliest collision point during the glide phase is κ3 and the latest collision point is κ4, and defining the altitude of point κ3 as h3, the blue team's missile flight time is t. 3b The Red Force missile's flight time is t. 3r At point κ4, the altitude is h4, and the Blue Force missile's flight time is t. 4b The Red Force missile's flight time is t. 4r .

[0110] It is easy to see that point κ2 is the separation point of the Blue Force missile's active phase. Assume the Blue Force missile's active phase separation point is t. 2b Altitude h2, the distance the Blue Force missile has traveled on the x-axis at this moment. 2b .

[0111] Assuming the anti-missile interceptor weapon re-enters orbit at an angle of attack α after deorbiting, and the altitude is h2, the red force missile's orbital time t is...2r From the red side's altitude-range curve, it can be seen that the red side's missile has traveled a distance x on the x-axis at this time. 2r .

[0112] Analysis reveals that the time difference t between the red and blue teams at this point is... △ :

[0113] t △ =t 2b -t 2r (34)

[0114] That is, the on-orbit motion time of the interceptor weapon is t. △ The formula for calculating the forward distance of the on-orbit motion at this time is:

[0115] △x 2r =v g ×t △ (35)

[0116] Specifically, when the orbital altitude is 120km, the interceptor weapon's on-orbit operating speed v g =7364m / s.

[0117] The distance between the red and blue teams can be calculated as x2:

[0118] x2=x 2b +x 2r +△x 2r (36)

[0119] Assuming the angle of attack is α, at t 2r At any given moment, the altitude h of the interceptor weapon. 2r Equivalent to the ideal interception point altitude h2, we obtain x 2r x 2b x2.

[0120] It can be seen that t 1r The time of the earliest collision point κ1 is used to obtain x. 2r x 2b 、x1.

[0121] In summary, the active segment interception window x can be obtained. z :

[0122] x z =[x1,x2] (37)

[0123] Based on the interceptor weapon capability specifications, the size of the lateral window during the active phase is tentatively set as follows: Through continuous iteration, the size of the lateral window during the active phase of the interceptor weapon was determined to be x. zc .

[0124] Theoretically, the earliest collision point κ3 of the gliding phase interception coincides with the latest collision point κ2 of the active phase interception, thus yielding x. 3r x 4b At this point, the distance between the red and blue sides at the earliest collision point κ3 during the gliding phase is x3:

[0125] x3=x 3r +x 3b (38)

[0126] It can be known that at κ4, t 4r Time x 4r x 4b At this point, the distance between the red and blue sides at the latest collision point κ4 during the gliding phase is x4:

[0127] x4=x 4r +x 4b (39)

[0128] Therefore, the glide segment interception window x can be obtained. h :

[0129] x h =[x3,x4] (40)

[0130] Based on the interceptor weapon capability specifications, the size of the lateral window during the active phase is tentatively set as follows: Through continuous iteration, the size of the lateral window during the active phase of the interceptor weapon was determined to be x. hc .

[0131] Step 3: Update the interceptor deployment;

[0132] The total window span difference for interception is △x:

[0133] △x=x4-x1 (41)

[0134] The longitude spanned along the equator is △l:

[0135] △l=△x / l0 (42)

[0136] Where l0 is the distance per unit longitude at the equator, and assuming a window contains at least n missiles, then we can obtain:

[0137] Number N of on-orbit interceptors distributed on a single track:

[0138] N=(360 / △l)×n (43)

[0139] Step 4: Optimize interceptor deployment;

[0140] If there is no interceptor in the current interception window, the interception deployment needs to be optimized.

[0141] The active segment window at this time is:

[0142] x z =[x1,x2] (44)

[0143] The gliding window at this time is:

[0144] x h =[x3,x4] (45)

[0145] Let the optimization variable be x. o The optimized active and gliding segment windows are as follows:

[0146]

[0147] At this point, the total window span difference for interception is △x':

[0148] △x'=x4-x1+2x o (47)

[0149] The longitude spanned along the equator is △l':

[0150] △l'=△x' / l0 (48)

[0151] Assuming a window contains at least n missiles, then we can obtain:

[0152] Number of on-orbit interceptors distributed on a single track, N':

[0153] N'=(360 / △l')×n (49)

[0154] Step 5: Derailment decision;

[0155] Suppose there are M interceptors, namely interceptor L1, L2...L... M They are all within the temporal and spatial interception windows, and the relative distances between each interceptor and the target can be obtained as R1, R2...R M .

[0156] The deorbit priority of each interceptor is sorted according to the principle of sorting the interceptors in ascending order of their relative distance from the target.

[0157] Assume interceptors L1, L2...L M The relationship between the relative distances to the target is as follows:

[0158] R1 <R2<…<R M (50)

[0159] The selection of interceptors is based on the interception scenario. Assuming that T (T≥1) interceptors are needed to intercept the target, the interceptors required for deorbiting and reentry interception are L1, ... L2. T .

[0160] Example:

[0161] Point κ2 is the separation point of the Blue Force's missile during its boost phase. Figure 2 , Figure 3 , Figure 4 The separation point t of the Blue Force's missile during the active phase can be obtained. 2b =100s, at this time h2 = 44000m, the distance the Blue Force missile has traveled on the x-axis of the launch system is x. 2b =178.185km.

[0162] Assume that after leaving the orbit, the red team re-enters the orbit at an angle of attack of α = 40°. Figure 5 Given that h2 = 44000m, the red missile's travel time t at this time is... 2r =85.64s, by Figure 6 It can be seen that the red missile's current launch distance along the x-axis is x. 2r =623.504km.

[0163] Analysis reveals that the time difference t between the red and blue teams at this point is... △ =t 2b -t 2r =14.36s, meaning the red force's weapon's on-orbit movement time is t. △ The formula for calculating the forward distance of the on-orbit motion at this time is:

[0164] △x 2r =v g ×t △ (51)

[0165] Based on previous verification, the weapon's on-orbit operating speed v g =7364m / s, and the calculated Δx 2r =105.747km.

[0166] The formula for calculating the distance x2 between the red and blue teams is as follows:

[0167] x2=x 2b +x 2r +△x 2r (52)

[0168] After calculation and integration, x2 = 908 km.

[0169] Considering the actual situation, it is difficult to balance the weapon when it enters the orbit with an attitude angle of α = 40°. Therefore, after a large number of simulation experiments, the following results were obtained:

[0170] When α = 12.5°, t 2r =100s, at which time the interceptor weapon's altitude h 2r =44000m, which is equivalent to the ideal interception point altitude h2 = 44000m, at which point x2r =712.24km,x 2b =178.185km, at this time x2 =890.425km.

[0171] Depend on Figure 7 Know: t 1r =86.9s is the time of the earliest collision point κ1. At this time, by Figure 8 , Figure 9 Know: x 2r =632.958km,x 2b =114.988km, so x1 =747.946km.

[0172] In summary, the active segment interception window [x1, x2] = [747.946, 890.425] km;

[0173] Based on the missile's capability specifications, the size of the lateral window during the active phase was initially set at 100km. After continuous iteration, the size of the lateral window during the active phase was determined to be 80km.

[0174] Theoretically, the earliest collision point κ3 during the gliding phase interception coincides with the latest collision point κ2 during the active phase interception, i.e., x 3r =712.24km,x 4b =178.185km, at which point the distance between the red and blue sides at the earliest collision point κ3 during the gliding phase is x3 = x 3r +x 3b =890.425km.

[0175] It can be known that at κ4, t 4r =900s, at this time x 4r =3250km,x 4b =2750km, at this point the distance between the red and blue sides at the latest collision point κ4 during the gliding phase is x4 = x 4r +x 4b =6000km.

[0176] Therefore, the interception window during the gliding phase is [x3, x4] = [890.425, 6000] km. After iterative iterations, the lateral window size during the active phase was determined to be 2500 km, initially set at 3000 km.

[0177] On-orbit interceptor single-track density calculation:

[0178] Total interception window span difference: Δx = x4 - x1 = 5252.054 km, which means the longitude spanned on the equator is Δl = Δx / 111 km ≈ 47.315°. Assuming that there are at least 8 space-based anti-missile interceptors in one window, we can obtain:

[0179] Number of single-track interceptors: N = (360 / Δl) × 8 = 60.8686, that is, the number of single-track interceptors is 61.

Claims

1. A method for interceptor deployment and de-orbit decision in a space-based anti-missile scenario, characterized in that, Comprising the following steps: Step 1: build a time interception window model; Step 1-1: For the blue side missile, the gliding flight trajectory is determined by its main phase shutdown point parameters (r k ,v k ,θ k ), and its flight trajectory is approximately regarded as an elliptical trajectory; according to the elliptical theory, the related parameters of the elliptical trajectory: the major semi-axis a, the minor semi-axis b, the eccentricity e and the half pitch P, the calculation formula is represented as: In the formula, r0 is the geocentric distance of the active segment shutdown point, v0 is the speed of the active segment shutdown point, and θ0 is the trajectory inclination angle of the active segment shutdown point; γ0 is called the energy parameter, and μ is the earth gravity coefficient; wherein: Step 1-2: Let the time of ballistic missile flying from perigee p to main active stage shutdown point k0, the earliest interception point k1 and the latest interception point k2 be t0, t1 and t2 respectively The perigee eccentric angles of ballistic missile flying from perigee p to main active stage shutdown point k0, the earliest interception point k1 and the latest interception point k2 are E0, E1 and E2 respectively, and according to Kepler equation: Then we get: In the formula, n represents the average movement per unit time, E represents the mean anomaly, and e represents the eccentricity of the orbit; Step 1-3: From formula (4), the time t k01 that the blue missile flies from the active phase shutdown point k0 to the earliest interception point k1 and the time t k02 that the blue missile flies to the latest interception point k2 are respectively: In the formula, E0, E1 and E2 are the mean anomaly corresponding to the target trajectory active segment shutdown point k0, the earliest interception point k1 and the latest interception point k2 respectively, and their calculation formulas are as follows: Wherein, r1 and r2 represent the geocentric distance of the earliest interception point k1 and the latest interception point k2 respectively; v1 and v2 represent the speed of the earliest interception point k1 and the latest interception point k2 respectively; At this point, the time window for the interception of Hongfang missiles is obtained as t w = [t0, t1] (7) Wherein: Step 2: build a space interception window; Step 2-1: Set the earliest collision point in the active section as κ1, the latest collision point as κ2, and define the elevation at the κ1 point as h1, the running time of the blue missile as t 1b , the running time of the red missile as t 1r ; the elevation at the κ2 point as h2, the running time of the blue missile as t 2b , the running time of the red missile as t 2r ; Let the earliest collision point in the gliding phase be κ3, the latest collision point be κ4, the altitude at the point κ3 be h3, the running time of the blue missile be t 3b , the running time of the red missile be t 3r ; the altitude at the point κ4 be h4, the running time of the blue missile be t 4b , the running time of the red missile be t 4r ; Then the point κ2 is the active stage separation point of the Blue Side missile, and the running time of the Blue Side missile at the active stage separation point is t 2b , the altitude is h2, and the Blue Side missile advances a distance x 2b in the x-axis of the launch system at this time. Step 2-2: When the anti-missile weapon enters the orbit with the angle of attack α, the running time of the red missile is t 2r According to the height-range curve of the red missile, the distance of the red missile in the x-axis of the launch system is x 2r ; At this time, the running time difference t between the red and blue sides △ : t △ = t 2b - t 2r (9) The time of intercepting the weapon in orbit is t △ At this time, the formula for calculating the forward distance of the in-orbit movement is: Δx 2r = v g × t △ (10) The distance x2 between the red and blue parties is obtained as x2= x 2b + x 2r + Δx 2r (11) Let the angle of attack be α, at time t 2r the altitude h 2r of the intercept weapon corresponds to the ideal intercept point altitude h2, obtaining x 2r , x 2b , x2; t 1r is the time of the earliest collision point κ1, obtaining x 2r , x 2b , x1; Summarized above is the intercept window x of the active segment z : x z = [x1, x2] (12) According to the intercept weapon capability index, the size of the active stage lateral window is temporarily set as x zc0 , through continuous iteration, the size of the intercept weapon active stage lateral window is determined as x zc ; Step 2-3: In theory, the glide phase intercepts the earliest collision point κ3, coincides with the active phase intercepting the latest collision point κ2, that is, x 3r , x 4b , at this time the red and blue distance of the glide phase earliest collision point κ3 is x3: x3 = x 3r + x 3b (13) At time t 4r The distance x 4r , x 4b between the red and blue parties at the latest impact point of the glide phase κ4 is x4: x4 = x 4r + x 4b (14) From this the glide phase intercept window x is derived h : x h = [x3, x4] (15) According to the intercept weapon capability index, the active stage lateral window size is first set as x hc0 , through continuous iteration, the intercept weapon active stage lateral window size is determined as x hc ; Step 3: update the interceptor deployment; The total window span difference is Δx: Δx=x4-x1 (16) Cross the longitude on the equator as Δl: △l＝△x / l0 (17) Where l0 is the distance of a unit longitude on the equator; Assuming that a window has at least n missiles, the single-track distribution number N of on-orbit interceptors is obtained as N=(360 / △l)×n (18) Step 4: optimize the interceptor deployment; When there is no interceptor in the current interception window, the active segment window at this time is: x z = [x1, x2] (19) The gliding segment window at this time is: x h = [x3, x4] (20) Let the optimization variable be x o The optimized active phase and gliding phase windows are: The total window span difference at this time is Δx': Δx' = x4 - x1 + 2x o (22) Cross the longitude on the equator as Δl': △l'＝△x' / l0 (23) Assuming that a window has at least n missiles, the single-track distribution number N' of on-orbit interceptors is obtained as N'=(360 / △l')×n (24) Step 5: deorbit decision; Step 5-1: There are M interceptors, which are interceptors L1, L2…L M , respectively. They are all within the time and space interception window, and the relative distances between each interceptor and the target are R1, R2…R M ; Step 5-2: prioritize the deorbit of each interceptor, with the sorting principle being: the relative distance between the interceptor and the target is sorted from small to large; Step 5-3: Set the interceptors L1, L2...L M The relationship with the target relative distance is: R1< R2<... < R M (25) According to the selection of the interceptor according to the interception scenario, if T interceptors are needed to intercept the target, the interceptors for the interception of the orbit departure and reentry are L1, …L T .

2. The interceptor deployment and deorbit decision method in a space-based anti-missile scenario according to claim 1, characterized in that, The T≥1.

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