CN111859526A - Method for quickly determining overall parameters of boosting gliding missile - Google Patents

Method for quickly determining overall parameters of boosting gliding missile Download PDF

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CN111859526A
CN111859526A CN202010497999.0A CN202010497999A CN111859526A CN 111859526 A CN111859526 A CN 111859526A CN 202010497999 A CN202010497999 A CN 202010497999A CN 111859526 A CN111859526 A CN 111859526A
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boosting
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CN111859526B (en
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江振宇
李俊
孙小东
樊晓帅
马润东
张士峰
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National University of Defense Technology
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Abstract

The invention provides a method for quickly determining overall parameters of a boosting gliding missile, which comprises the following steps: inputting a target range of the missile, and dividing the trajectory into a boosting section, an adjusting section, a gliding section and a final guiding section; calculating the range of each section according to the position and speed requirements of the ballistic transition point; accumulating the ranges of the boosting section, the adjusting section and the gliding section to obtain a total range, comparing the total range with a target range, and performing iterative solution to ensure that the total range meets the requirement of the target range, thereby determining a target trajectory; obtaining a trajectory parameter estimation value according to a target trajectory; then, obtaining a shutdown point structure ratio and the quality requirement of the missile according to the target trajectory to obtain a quality parameter estimation value; and obtaining a power parameter estimated value according to the quality parameter estimated value. The method for rapidly determining the general parameters of the boosted gliding missile provided by the invention adopts segmented ballistic computation, reasonable assumption and application of empirical formulas, and can greatly improve the computation speed and efficiency on the premise of ensuring certain solving precision.

Description

Method for quickly determining overall parameters of boosting gliding missile
Technical Field
The invention relates to the technical field of aircrafts, in particular to a method for quickly determining general parameters of a boosting gliding missile.
Background
The boosting gliding missile adopts a booster to boost the missile to a certain height, separates a gliding body after reaching a certain speed, and the gliding body effectively utilizes the aerodynamic lift force to carry out long-distance maneuvering gliding flight in the atmosphere, has the advantages of long range, high precision, maneuvering flexibility and the like, and becomes a research hotspot of the current missile weapons.
The design of the overall parameters of the missile is the basis of missile design, and the rapid acquisition of the overall parameters in the scheme demonstration stage is beneficial to improving the overall design efficiency and shortening the design period. The existing overall parameter design method is mainly directed at the ballistic missile, and because the ballistic vertex height of the ballistic missile is higher and the reentry process does not need to depend on aerodynamic force to maneuver and fly, the target ballistic trajectory can be quickly solved by simply dividing the ballistic trajectory into three sections, namely an active section, a reentry section and a final guide section, by fully utilizing the vacuum flight assumption in the ballistic trajectory solving process. The trajectory vertex of the boosting gliding missile is mostly within 60km, the range covering capability mainly depends on the capability of a gliding body in the atmosphere for maneuvering gliding flight by utilizing aerodynamic force, on one hand, the boosting gliding missile flies in the atmosphere almost in the whole course, the vacuum flight assumption is not established, and the trajectory solving method based on the vacuum flight assumption cannot be applied; on the other hand, the boosted gliding missile has larger difference with the channel type missile in the aspect of the ballistic characteristics, the ballistic is simply divided into three sections of an active section, a reentry section and a final guide section for ballistic solution, the introduced system has larger error, the reliability of a calculation result is low, and the requirement of solution precision cannot be met.
Disclosure of Invention
The invention aims to provide a method for quickly determining power parameters of a boosting gliding missile so as to solve the technical problems in the prior art.
In order to achieve the aim, the invention provides a method for quickly determining the overall parameters of a boosting gliding missile, which comprises the following steps:
inputting a target range of the missile, and dividing the trajectory into a boosting section, an adjusting section, a gliding section and a final guiding section; inputting a speed position parameter of each shift point of the trajectory and the average lift-drag ratio of the glide section; the speed position parameters of each shift crossing point of the trajectory comprise the height of a shutdown point of the boosting section, the height of a vertex of the trajectory and the final speed;
calculating the state parameters of each flight crossing point and the range of each section of the boosting section, the adjusting section and the gliding section according to the speed position parameters of each flight crossing point of the trajectory and a preset empirical formula; the state parameters of the shift crossing point comprise the speed of the shutdown point, the speed inclination angle and the ballistic vertex speed;
accumulating the range of each section of the boosting section, the adjusting section, the gliding section and the final guide section to obtain a total range, comparing the total range with the target range, and performing iterative solution to ensure that the total range meets the target range requirement and determine a target trajectory;
obtaining a ballistic parameter estimation value according to the target ballistic; the ballistic parameter estimated value comprises a shutdown point speed, a speed inclination angle, a ballistic vertex speed and each range;
Obtaining a quality parameter estimation value according to the trajectory parameter estimation value and the trajectory quality requirement;
and obtaining a power parameter estimated value according to the quality parameter estimated value.
Further, calculating the state parameters of each flight point and the range of each section of the boosting section, the adjusting section and the gliding section according to the speed position parameters of each flight point of the trajectory and a preset empirical formula, and the method comprises the following steps:
according to the input speed and position parameters of the shift change point: boost section shutdown point height h1Height h of trajectory vertex2Terminal velocity v3And the average lift-drag ratio lambda of the glide section, and calculating to obtain the speed v of the shutdown point1Angle of inclination of speed theta1And ballistic peak velocity v2(ii) a Input boost engine specific impulse IspCalculating each range respectively as follows:
calculating the flight range of the glide section:
from empirical formulas, directlyObtaining the flight range R of the glide section3Is composed of
R3＝0.6R
Wherein R is the target range;
estimation of the slip speed:
through the glide range of flight R3Approximate formula
Figure BDA0002523664770000021
Thereby obtaining a slip velocity v2Is composed of
Figure BDA0002523664770000022
Wherein, the average lift-drag ratio lambda of the glide section and the universal gravitation constant g are 9.8 m/s;
estimating the shutdown point speed of the boosting section:
assuming no energy loss in the adjustment section, the formula of energy conservation
Figure BDA0002523664770000031
Thereby obtaining the speed v of the shutdown point 1Is composed of
Figure BDA0002523664770000032
Wherein r is1The distance from the shutdown point to the geocenter is represented by the formula r1＝h1+r0Obtaining r2The distance from the top point of the trajectory to the center of the earth is represented by the formula r2＝h2+r0Find the radius r of the earth0Taking 6371 km;
estimating the speed inclination angle of a shutdown point of the boosting section:
calculating formula according to orbit eccentricity e and energy parameter upsilon
Figure BDA0002523664770000033
υ＝v2r
Thereby obtaining the speed inclination angle theta of the shutdown point1Is composed of
Figure BDA0002523664770000034
Estimating the range of the adjustment section:
according to Kepler's equation
r＝a(1-ecosE)
Thereby obtaining a deviation angle
Figure BDA0002523664770000035
Wherein r is the distance between the centers of the earth and the semi-major axis a of the elliptical orbit can be defined by
Figure BDA0002523664770000036
Obtained and respectively substituted into r1、r2The value can be obtained to obtain the corresponding approximate point angle E of the shutdown point1Angle of approach E corresponding to the vertex of trajectory2；
Further obtain the range R of the adjustment section2Is composed of
R2＝E2-E1
Estimating the range of the boosting section:
the change rule of the trajectory inclination angle of the boosting section is assumed to be
Figure BDA0002523664770000037
Then
Figure BDA0002523664770000041
Wherein
Figure BDA0002523664770000042
Figure BDA0002523664770000043
Wherein, IspTo boost the engine ground specific impulse, h1The structure ratio mu of the shutdown point of the boosting section is obtained by substituting the height of the shutdown point of the boosting sectionkFurther obtain the boost range R1。
Further, accumulating the range of each section of the boosting section, the adjusting section, the gliding section and the final guiding section to obtain a total range R ', comparing the total range R ' with a target range R, and performing iteration in a circulating manner, wherein when R ' -R is less than finishing the circulation, the target trajectory is determined to obtain the target trajectory parameters; where is the accuracy of the calculation.
Further, obtaining a mass parameter estimation value according to the ballistic parameter estimation value and the ballistic mass requirement, including:
according to the input gliding mass mhBoost engine quality factor alphaenThe quality factor N of the tail section of the missile and the structure ratio mu of the shutdown point of the boosting section estimated by the trajectory integral modulekEstimating the takeoff mass m of the missile0And boosting engine charge mfuelThe method comprises the following steps:
flying mass m of missile0The calculation of (2):
according to the missile mass formula
m0＝mh+(1-μk)m0+(1-μk)αenm0+Nm0
Available missile takeoff mass m0Is composed of
Figure BDA0002523664770000044
Wherein the mass m of the gliding masshBoost engine quality factor alphaenThe quality factor N of the tail section of the missile is known as input, and the shutdown point structure ratio mu of the boosting section iskThe result is obtained in step three.
Boosting engine charge mfuelThe calculation of (2):
according to a boosted engine quality factor alphaenDirect calculationBoosting engine charge mfuelIs composed of
mfuel＝αenm0。
Further, obtaining a power parameter estimation value according to the quality parameter estimation value includes:
according to the initial thrust-weight ratio k of the input missile and the specific impulse I of the boosting enginespPropellant density rho of boosting engine, filling coefficient Z of boosting engine, missile outer diameter D and tail section length L of boosting enginepEstimating the ground thrust P and the mass flow rate m of the boosting engine sCombustion time tbAnd an engine length L; the method comprises the following specific steps:
calculation of the boosted engine ground thrust P:
the ground thrust P of the boosting engine is calculated by the formula
P＝km0g0
Wherein the initial thrust-weight ratio k of the missile is known, and the takeoff mass m of the missile0In the fourth step, the gravity constant g of sea level is obtained0Taking 9.8 m/s;
boost engine mass flow rate msThe calculation of (2):
boost engine mass flow rate msIs calculated by the formula
Figure BDA0002523664770000051
Wherein, the boosting engine has a specific impulse IspIs a known input;
time of combustion tbThe calculation of (2):
boost engine combustion time tbIs calculated by the formula
Figure BDA0002523664770000052
Calculation of engine length L:
the propellant volume V, which can be derived from the propellant density ρ of the boosted engine, is
Figure BDA0002523664770000053
Wherein the boost engine fill factor Z is a known input;
the boosting engine has a sectional area S of
Figure BDA0002523664770000061
The boosted engine length L can be calculated as
Figure BDA0002523664770000062
Wherein, the length L of the tail section of the boosting enginepIs a known input.
The invention has the following beneficial effects:
(1) according to the method for quickly determining the overall parameters of the boosting gliding missile, provided by the invention, the target trajectory is solved by dividing the missile flight trajectory into four sections, namely a boosting section, an adjusting section, a gliding section and a final guide section, so that the trajectory flight characteristics of the boosting gliding missile are better met, and the requirement on the accuracy of the target trajectory solution is met. The method specifically comprises the following steps: the target trajectory meeting the range requirement is obtained through iterative solution, then a missile overall structure parameter solution method from the target trajectory to trajectory parameters, mass parameters, power parameters and the like is established on the basis of the target trajectory, and the solution accuracy of the missile overall parameters is directly determined by the calculation accuracy of the target trajectory, so that the method can realize the fast, efficient and high-accuracy solution of the overall parameters of the boosting gliding missile. The method for quickly determining the overall parameters is mainly applied to early-stage overall design of the boosted gliding missile, can quickly calculate the overall parameters such as target trajectory, quality parameters, power parameters and the like through inputting tactical performance indexes, provides calculation basis and design direction for warhead design, cabin section layout, engine type selection and the like in the overall design process of the boosted gliding missile, and has great reference significance for the overall design of the missile.
(2) According to the method for rapidly determining the overall parameters of the boosting gliding missile, provided by the invention, the target trajectory is solved based on four sections, namely the boosting section, the adjusting section, the gliding section and the final guide section, and the vacuum flight assumption and the empirical formula are used more reasonably, so that the calculation speed and efficiency are greatly improved on the premise of ensuring certain solving precision. The missile overall parameter solution firstly determines a standard trajectory, the solution precision of the standard trajectory directly determines the calculation precision of subsequent overall parameters, if the boosting gliding missile trajectory is solved like a channel type missile in a three-section mode of an active section, a reentry section and a final guide section, the introduced system error is large, and the reliability of a calculation result is low; the trajectory is divided into four sections, namely a boosting section, an adjusting section, a gliding section and a final guide section, so that the trajectory flight characteristics of the boosting gliding missile are better met, the accuracy of a solution result is higher, and the reference significance to the overall design is greater.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a method flow diagram of a method of the present invention for rapidly determining a power parameter of a boosted gliding missile;
fig. 2 is a schematic diagram of a trajectory segment adopted by the method for rapidly determining the power parameter of the push-glide missile according to the invention.
Detailed Description
Embodiments of the invention will be described in detail below with reference to the drawings, but the invention can be implemented in many different ways, which are defined and covered by the claims.
Referring to fig. 1 to 2, the invention provides a method for rapidly determining the overall parameters of a boosting gliding missile, which comprises the following steps:
the method comprises the following steps: inputting missile target range
Inputting a target range of the missile, and dividing the trajectory into a boosting section, an adjusting section, a gliding section and a final guiding section; inputting a speed position parameter of each shift point of the trajectory and the average lift-drag ratio of the glide section; the velocity and location parameters for each handoff point of the trajectory include boost segment shutdown point height, trajectory apex height, and terminal velocity.
Step two: ballistic parameter estimation
Calculating the state parameters of each flight crossing point and the range of each section of the boosting section, the adjusting section and the gliding section according to the speed position parameters of each flight crossing point of the trajectory and a preset empirical formula;
the state parameters of each shift point include the speed of the shutdown point, the speed dip angle and the ballistic vertex speed.
Step three: judging whether the range requirement is met
Accumulating the range of each section of the boosting section, the adjusting section, the gliding section and the final guide section to obtain a total range, comparing the total range with the target range, and performing iterative solution to ensure that the total range meets the target range requirement and determine a target trajectory;
obtaining a ballistic parameter estimation value according to the target ballistic; the ballistic parameter estimated values comprise the speed of a shutdown point, the speed inclination angle, the top velocity of a ballistic trajectory and the range of each section.
Step four: quality parameter estimation
And obtaining a quality parameter estimated value according to the ballistic parameter estimated value and the ballistic quality requirement. The quality parameters comprise missile takeoff quality and boosting engine loading.
Specifically, a shutdown point structure ratio can be obtained according to target trajectory determination in the third step, and quality parameters such as takeoff quality, loading amount and the like are calculated according to the input quality factors of all parts and trajectory quality requirements.
Step five: dynamic parameter estimation
And obtaining a power parameter estimated value according to the quality parameter estimated value. The power parameters include boost engine ground thrust P, mass flow rate, combustion time, and engine length.
Specifically, according to the estimated values of the takeoff quality and the charge amount in the fourth step, the power parameters such as ground thrust, engine combustion time and the like can be calculated by utilizing the input initial thrust-weight ratio, specific impulse, fuel density, charge coefficient and the like of the boosting engine.
The method for rapidly determining the power parameters of the boosting gliding missile is explained by combining a specific embodiment, and specifically comprises the following steps:
the method comprises the following steps: inputting a target range R (400km), and dividing the trajectory into a boosting section, an adjusting section, a gliding section and a final guide section range according to an empirical formula; inputting the speed position parameter requirement of each shift point of the trajectory and the average lift-drag ratio of the glide section; the speed position parameters of each shift point of the trajectory comprise the boosting section shutdown point height, the trajectory vertex height and the final speed.
Step two: according to the shift point speed position input in the step one: boost section shutdown point height h1(23.8km), ballistic apex height h2(45km), final velocity v3(500m/s) and the average lift-drag ratio lambda (2.6) of the glide section, and the speed v at the shutdown point is calculated1(1603m/s), velocity tilt angle θ1(23.2 °) ballistic peak velocity (i.e., slip velocity) v2(1469 m/s). Input boost engine specific impulse Isp(2350Ns/kg), the ranges of all the sections can be respectively calculated as follows:
s1, calculating the flight range of the glide section by an empirical formula3Is composed of
R3＝0.6R
S2, estimating the slip speed:
through the glide range of flight R3Approximate formula
Figure BDA0002523664770000081
Thereby obtaining a slip velocity v 2Is composed of
Figure BDA0002523664770000082
Wherein, the average lift-drag ratio lambda of the glide section and the universal gravitation constant g are 9.8 m/s.
S3, estimating shutdown point speed of boosting section
Assuming no energy loss in the adjustment section, the formula of energy conservation
Figure BDA0002523664770000083
Thereby obtaining the speed v of the shutdown point1Is composed of
Figure BDA0002523664770000084
Wherein r is1The distance from the shutdown point to the geocenter is represented by the formula r1＝h1+r0Obtaining r2The distance from the top point of the trajectory to the center of the earth is represented by the formula r2＝h2+r0Find the radius r of the earth0Take 6371 km.
S4, estimating the shutdown point speed inclination angle of the boosting section
Calculating formula according to orbit eccentricity e and energy parameter upsilon
Figure BDA0002523664770000091
υ＝v2r
Thereby obtaining the speed inclination angle theta of the shutdown point1Is composed of
Figure BDA0002523664770000092
S5, estimating the range of the adjustment segment
According to Kepler's equation
r＝a(1-ecosE)
Thereby obtaining a deviation angle
Figure BDA0002523664770000093
Wherein r is the distance between the centers of the earth and the semi-major axis a of the elliptical orbit can be defined by
Figure BDA0002523664770000094
Obtained and respectively substituted into r1、r2The value can be obtained to obtain the corresponding approximate point angle E of the shutdown point1Angle of approach E corresponding to the vertex of trajectory2。
Further obtain the range R of the adjustment section2Is composed of
R2＝E2-E1
S6, estimating boost range
The change rule of the trajectory inclination angle of the boosting section is assumed to be
Figure BDA0002523664770000095
Then
Figure BDA0002523664770000096
Wherein
Figure BDA0002523664770000101
Figure BDA0002523664770000102
Wherein, IspTo boost the engine ground specific impulse, h1The structure ratio mu of the shutdown point of the boosting section is obtained by substituting the height of the shutdown point of the boosting sectionkFurther obtain the boost range R1。
Step three: and step two, a loop iteration step, namely ending the loop when the designed range meets the requirement of the target range, and determining a whole-range ballistic scheme (the boost section range is 54km, the adjusting section range is 93km and the gliding section range is 253 km). The method specifically comprises the following steps: estimating a total range R' of
R＝R1+R2+R3
When R' -R < finish loop, the calculation precision is the same.
It should be noted that, since the reachable range of the boosted gliding missile is mainly borne by the boosting section, the adjusting section and the gliding section, and the terminal guidance section occupies a smaller proportion in the total range, the range of the terminal guidance section can be ignored when estimating the total range. If the influence of the final range is really needed to be considered, the input value can be properly reduced when the target range is input in the first step, and the margin of the final range is reserved.
Step four: according to the input gliding mass mh(480kg), boost Engine quality factor αen(0.1), the missile tail section quality factor N (0.01), and the boost section shutdown point structure ratio mu estimated by the trajectory integration modulekEstimating the takeoff mass m of the missile0(2221kg) boosting Engine Loading mfuel(1563kg) and the like. The method comprises the following specific steps:
(1) calculating takeoff mass
According to the missile mass formula
m0＝mh+(1-μk)m0+(1-μk)αenm0+Nm0
Available missile takeoff mass m0Is composed of
Figure BDA0002523664770000103
Wherein the mass m of the gliding masshBoost engine quality factor alphaenThe quality factor N of the tail section of the missile is known as input, and the shutdown point structure ratio mu of the boosting section iskThe result is obtained in step three.
(2) Calculating the amount of charge
According to a boosted engine quality factor alphaenDirectly calculating the loading m of boosting engine fuelIs composed of
mfuel＝αenm0
Step five: according to the input missile initial thrust-weight ratio k (3.2) and boosting engine specific impulse Isp(2350Ns/kg), propellant density rho (1750kg/m3) of boosting engine, loading coefficient Z (0.86) of boosting engine, external diameter D (600mm) of missile, and length L of tail section of boosting enginep(0.7m), estimating the boosted engine ground thrust P (69639N), mass flow rate ms(29.6kg/s) and combustion time tb(52.7s) and the engine length L (3.67 m). The method comprises the following specific steps:
(1) estimating ground thrust
The ground thrust P of the boosting engine is calculated by the formula
P＝km0g0
Wherein the initial thrust-weight ratio k of the missile is known, and the takeoff mass m of the missile0In the fourth step, the gravity constant g of sea level is obtained0The ratio was 9.8 m/s.
(2) Estimating mass flow rate
Boost engine mass flow rate msIs calculated by the formula
Figure BDA0002523664770000111
Wherein, the boosting engine has a specific impulse IspIs a known input.
(3) Estimating combustion time
Boost engine combustion time tbIs calculated by the formula
Figure BDA0002523664770000112
Wherein, the boosting engine has the charge mfuelThe result is obtained in step four.
(4) Estimating the engine length from the propellant density rho of the boosted engine to obtain the volume V of the propellant
Figure BDA0002523664770000113
Where the boosted engine fill factor Z is a known input.
The boosting engine has a sectional area S of
Figure BDA0002523664770000121
The boosted engine length L can be calculated as
Figure BDA0002523664770000122
Wherein, the length L of the tail section of the boosting enginepIs a known input.
In conclusion, the invention provides a method for rapidly determining the overall parameters of a boosting gliding missile, which solves the target trajectory based on four sections of a boosting section, an adjusting section, a gliding section and a final guiding section, and reasonably uses a vacuum flight hypothesis and an empirical formula, thereby greatly improving the calculation speed and efficiency on the premise of ensuring certain solution precision. The missile overall parameter solution firstly determines a standard trajectory, the solution precision of the standard trajectory directly determines the calculation precision of subsequent overall parameters, if the boosting gliding missile trajectory is solved like a channel type missile in a three-section mode of an active section, a reentry section and a final guide section, the introduced system error is large, and the reliability of a calculation result is low; the trajectory is divided into four sections, namely a boosting section, an adjusting section, a gliding section and a final guide section, so that the trajectory flight characteristics of the boosting gliding missile are better met, the accuracy of a solution result is higher, and the reference significance to the overall design is greater.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (5)

1. The method for quickly determining the overall parameters of the boosting gliding missile is characterized by comprising the following steps of:
inputting a target range of the missile, and dividing the trajectory into a boosting section, an adjusting section, a gliding section and a final guiding section; inputting a speed position parameter of each shift point of the trajectory and the average lift-drag ratio of the glide section; the speed position parameters of each shift crossing point of the trajectory comprise the height of a shutdown point of the boosting section, the height of a vertex of the trajectory and the final speed;
calculating the state parameters of each flight crossing point and the range of each section of the boosting section, the adjusting section and the gliding section according to the speed position parameters of each flight crossing point of the trajectory and a preset empirical formula; the state parameters of the shift crossing point comprise the speed of the shutdown point, the speed inclination angle and the ballistic vertex speed;
accumulating the range of each section of the boosting section, the adjusting section, the gliding section and the final guide section to obtain a total range, comparing the total range with the target range, and performing iterative solution to ensure that the total range meets the target range requirement and determine a target trajectory;
obtaining a ballistic parameter estimation value according to the target ballistic; the ballistic parameter estimated value comprises a shutdown point speed, a speed inclination angle, a ballistic vertex speed and each range;
obtaining a quality parameter estimation value according to the trajectory parameter estimation value and the trajectory quality requirement;
And obtaining a power parameter estimated value according to the quality parameter estimated value.
2. The method for rapidly determining the overall parameters of the boosting gliding missile according to claim 1, wherein the step of calculating the state parameters of each flight point and the range of each of the boosting section, the adjusting section and the gliding section according to the speed and position parameters of each flight point of the trajectory and a preset empirical formula comprises the following steps:
according to the input speed and position parameters of the shift change point: boost section shutdown point height h1Height h of trajectory vertex2Terminal velocity v3And the average lift-drag ratio lambda of the glide section, and calculating to obtain the speed v of the shutdown point1Angle of inclination of speed theta1And ballistic peak velocity v2(ii) a Input boost engine specific impulse IspRespectively calculating the range of each section, which comprises the following steps:
calculating the flight range of the glide section:
directly obtaining the flight range R of the glide section by an empirical formula3Is composed of
R3＝0.6R
Wherein R is the target range;
estimation of the slip speed:
through the glide range of flight R3Approximate formula
Figure FDA0002523664760000011
Thereby obtaining a slip velocity v2Is composed of
Figure FDA0002523664760000021
Wherein, the average lift-drag ratio lambda of the glide section and the universal gravitation constant g are 9.8 m/s;
estimating the shutdown point speed of the boosting section:
assuming no energy loss in the adjustment section, the formula of energy conservation
Figure FDA0002523664760000022
Thereby obtaining the speed v of the shutdown point 1Is composed of
Figure FDA0002523664760000023
Wherein r is1The distance from the shutdown point to the geocenter is represented by the formula r1＝h1+r0Obtaining r2The distance from the top point of the trajectory to the center of the earth is represented by the formula r2＝h2+r0Find the radius r of the earth0Taking 6371 km;
estimating the speed inclination angle of a shutdown point of the boosting section:
calculating formula according to orbit eccentricity e and energy parameter upsilon
Figure FDA0002523664760000024
υ＝v2r
Thereby obtaining the speed inclination angle theta of the shutdown point1Is composed of
Figure FDA0002523664760000025
Estimating the range of the adjustment section:
according to Kepler's equation
r＝a(1-ecosE)
Thereby obtaining a deviation angle
Figure FDA0002523664760000026
Wherein r is the distance between the centers of the earth and the semi-major axis a of the elliptical orbit can be defined by
Figure FDA0002523664760000031
Obtained and respectively substituted into r1、r2The value can be obtained to obtain the corresponding approximate point angle E of the shutdown point1Angle of approach E corresponding to the vertex of trajectory2；
Further obtain the range R of the adjustment section2Is R2＝E2-E1
Estimating the range of the boosting section:
the change rule of the trajectory inclination angle of the boosting section is assumed to be
Figure FDA0002523664760000032
Then
Figure FDA0002523664760000033
Wherein
Figure FDA0002523664760000034
Figure FDA0002523664760000035
Wherein, IspTo boost the engine ground specific impulse, h1The structure ratio mu of the shutdown point of the boosting section is obtained by substituting the height of the shutdown point of the boosting sectionkFurther obtain the boost range R1。
3. The method for rapidly determining the overall parameters of the boosting gliding missile as claimed in claim 1, wherein the ranges of each of the boosting section, the adjusting section, the gliding section and the final guiding section are accumulated to obtain a total range R ', the total range R ' is compared with a target range R, iteration is performed in a cycle, and when the absolute value of R ' -R < the end of the cycle, a target trajectory is determined to obtain the target trajectory parameters; where is the accuracy of the calculation.
4. The method for rapidly determining the overall parameters of a boosting gliding missile according to claim 1, wherein the step of obtaining the estimated value of the mass parameters according to the estimated value of the ballistic parameters and the mass requirement of the ballistic trajectory comprises the following steps:
according to the input gliding mass mhBoost engine quality factor alphaenThe quality factor N of the tail section of the missile and the structure ratio mu of the shutdown point of the boosting section estimated by the trajectory integral modulekEstimating the takeoff mass m of the missile0And boosting engine charge mfuelThe method comprises the following steps:
flying mass m of missile0The calculation of (2):
according to the missile mass formula
m0＝mh+(1-μk)m0+(1-μk)αenm0+Nm0
Available missile takeoff mass m0Is composed of
Wherein the mass m of the gliding masshBoost engine quality factor alphaenThe quality factors N of the tail sections of the missiles are all known as input mukThe structure ratio of the shutdown point of the boosting section is;
boosting engine charge mfuelThe calculation of (2):
according to a boosted engine quality factor alphaenDirectly calculating the loading m of boosting enginefuelIs composed of
mfuel＝αenm0。
5. The method for rapidly determining the overall parameters of a boosted gliding missile as claimed in claim 4, wherein obtaining the estimated power parameter value according to the estimated quality parameter value comprises:
according to the initial thrust-weight ratio k of the input missile and the specific impulse I of the boosting engine spPropellant density rho of boosting engine, filling coefficient Z of boosting engine, missile outer diameter D and tail section length L of boosting enginepEstimating the ground thrust P and the mass flow rate m of the boosting enginesCombustion time tbAnd an engine length L, as follows:
calculation of the boosted engine ground thrust P:
the ground thrust P of the boosting engine is calculated by the formula
P＝km0g0
Wherein the initial thrust-weight ratio k of the missile is known, m0The gravitational constant g of sea level for the takeoff mass of missile0Taking 9.8 m/s;
boost engine mass flow rate msThe calculation of (2):
boost engine mass flow rate msIs calculated by the formula
Figure FDA0002523664760000051
Wherein, the boosting engine has a specific impulse IspIs a known input;
time of combustion tbThe calculation of (2):
boost engine combustion time tbIs calculated by the formula
Figure FDA0002523664760000052
Calculation of engine length L:
the propellant volume V, which can be derived from the propellant density ρ of the boosted engine, is
Figure FDA0002523664760000053
Wherein the boost engine fill factor Z is a known input;
the boosting engine has a sectional area S of
Figure FDA0002523664760000054
The boosted engine length L can be calculated as
Figure FDA0002523664760000055
Wherein, the length L of the tail section of the boosting enginepIs a known input.
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