CN111859526B - Method for quickly determining overall parameters of boosting and gliding missile - Google Patents
Method for quickly determining overall parameters of boosting and gliding missile Download PDFInfo
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Abstract
The invention provides a method for quickly determining overall parameters of a boosting and gliding missile, which comprises the following steps: inputting the target range of the missile, and dividing the trajectory into a boosting section, an adjusting section, a gliding section and a terminal guidance section; according to the position and speed requirements of the ballistic shift points, calculating the range of each section; 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 iteratively solving to ensure that the total range meets the target range requirement, thereby determining a target trajectory; obtaining a ballistic parameter estimated value according to the target trajectory; obtaining a shutdown point structure ratio and the quality requirement of the missile according to the target trajectory to obtain a quality parameter estimated value; and obtaining a power parameter estimated value according to the quality parameter estimated value. The method for quickly determining the overall parameters of the boosting and gliding missile provided by the invention adopts the sectional trajectory calculation, reasonable assumption and application of an empirical formula, and can greatly improve the calculation speed and efficiency on the premise of ensuring a certain solving precision.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a method for quickly determining overall parameters of a boosted and gliding missile.
Background
The booster gliding missile adopts a booster to push the missile to a certain height, and separates the gliding body after the missile reaches a certain speed, the gliding body effectively utilizes aerodynamic lift to do long-distance maneuvering gliding flight in the atmosphere, and the booster gliding missile has the advantages of long range, high precision, maneuvering flexibility and the like, and becomes a research hot spot of the current missile weapon.
The design of the overall parameters of the missile is the basis of the design of the missile, 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 current overall parameter design method is mainly aimed at a ballistic missile, and the ballistic missile has higher ballistic vertex height and does not depend on aerodynamic force to maneuver and glide to fly in the reentry process, so that vacuum flight assumption can be fully utilized in the ballistic solving process, and the ballistic trajectory is simply divided into three sections, namely an active section, a reentry section and a terminal guidance section, so that the target trajectory can be quickly solved. The ballistic vertex of the boosting glider is mostly within 60km, the range coverage capability mainly depends on the capability of the glider to make maneuvering glider fly in the atmosphere by utilizing aerodynamic force, on one hand, the boosting glider almost flies in the atmosphere 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 boost gliding missile has larger difference with the ballistic missile in the aspect of ballistic characteristic, the trajectory is simply divided into an active section, a reentry section and a terminal guidance section for carrying out ballistic solution, the introduced system error is larger, the reliability of the calculation result is low, and the requirement of solving precision cannot be met.
Disclosure of Invention
The invention aims to provide a method for quickly determining power parameters of a boosting and gliding missile, which aims to solve the technical problems in the prior art.
In order to achieve the above purpose, the invention provides a method for rapidly determining the overall parameters of a booster and gliding missile, which comprises the following steps:
Inputting the target range of the missile, and dividing the trajectory into a boosting section, an adjusting section, a gliding section and a terminal guidance section; and inputting speed position parameters of each shift point of the trajectory and average lift-drag ratio of the gliding section; the speed position parameters of each shift point of the trajectory comprise the height of the shutdown point of the boosting section, the height of the vertex of the trajectory and the final speed;
calculating state parameters of each shift point and the range of each of the boosting section, the adjusting section and the gliding section according to the speed position parameters of each shift point of the trajectory and a preset empirical formula; the state parameters of the shift points comprise shutdown point speed, speed dip angle and ballistic vertex speed;
Accumulating the ranges of each of the boosting section, the adjusting section, the gliding section and the terminal guidance section to obtain a total range, comparing the total range with a target range, and iteratively solving to ensure that the total range meets the target range requirement and determine a target trajectory;
obtaining a ballistic parameter estimated value according to the target trajectory; the trajectory parameter estimation value comprises a shutdown point speed, a speed dip angle, a trajectory vertex speed and each range;
obtaining a quality parameter estimation value according to the ballistic parameter estimation value and the ballistic quality requirement;
And obtaining a power parameter estimated value according to the quality parameter estimated value.
Further, according to the speed position parameters of each shift point of the trajectory and a preset empirical formula, calculating the state parameters of each shift point and the range of each section of the boosting section, the adjusting section and the gliding section, including:
According to the input shift-point speed position parameters: the power-off point height h 1, the ballistic vertex height h 2, the tail speed v 3 and the average lift-drag ratio lambda of the gliding section are calculated to obtain the power-off point speed v 1, the speed dip angle theta 1 and the ballistic vertex speed v 2; inputting a specific impulse I sp of the boosting engine, and respectively calculating the range of each section, wherein the specific impulse I sp is as follows:
calculation of glide range:
The range R 3 of the glide segment is directly obtained by an empirical formula
R3＝0.6R
Wherein R is the target range;
estimation of slip speed:
by approximating the formula with the range R 3 of the glide segment
Thereby obtaining the slip velocity v 2 as
Wherein, the average lift-drag ratio lambda of the gliding section, the gravitational constant g takes 9.8m/s;
Estimating the speed of a power-off point of a boosting section:
assuming no energy loss in the adjusting section, the energy conservation formula
Thereby obtaining the shutdown point speed v 1 as
Wherein r 1 is the distance from the shutdown point to the earth center and is obtained by a formula r 1＝h1+r0, r 2 is the distance from the ballistic vertex to the earth center and is obtained by a formula r 2＝h2+r0, and the earth radius r 0 is 6371km;
Estimating the speed and inclination angle of a power-off point of the boosting section:
According to the calculation formula of the track eccentricity e and the energy parameter upsilon
υ＝v2r
Thereby obtaining the shutdown point speed inclination angle theta 1 as
Estimation of the adjustment range:
According to kepler equation
r＝a(1-ecosE)
Thereby obtaining a near point angle
Wherein r is the ground center distance, and the semimajor axis a of the elliptical orbit can be defined byObtaining a corresponding close point angle E 1 at a shutdown point and a corresponding close point angle E 2 at a ballistic vertex by substituting r 1、r2;
Thereby obtaining the adjustment range R 2 as
R2＝E2-E1
Estimation of boost range:
assume that the variation rule of the trajectory inclination angle of the boosting section is
Then
Wherein the method comprises the steps of
Wherein, I sp is the ground specific impulse of the boosting engine, h 1 is the height of the shutdown point of the boosting section, and the structural ratio mu k of the shutdown point of the boosting section can be obtained, so that the range R 1 of the boosting section is obtained.
Further, accumulating the ranges of each of the boosting section, the adjusting section, the gliding section and the terminal guidance section to obtain a total range R ', comparing the total range R with a target range R, performing loop iteration, and ending the loop when |R' -R| < epsilon, and determining a target trajectory to obtain the target trajectory parameter; where ε is the accuracy of the calculation.
Further, obtaining a quality parameter estimation value according to the ballistic parameter estimation value and the ballistic quality requirement, including:
According to the input glide mass m h, the booster engine quality factor alpha en, the missile tail section quality factor N and the booster section shutdown point structure ratio mu k estimated by the trajectory integration module, the missile take-off mass m 0 and the booster engine loading m fuel are estimated, and the specific steps are as follows:
Calculation of missile take-off quality m 0:
According to the missile mass formula
m0＝mh+(1-μk)m0+(1-μk)αenm0+Nm0
The available missile take-off mass m 0 is
The mass m h of the gliding mass, the quality factor alpha en of the boosting engine and the quality factor N of the tail section of the missile are all known as inputs, and the shutdown point structure ratio mu k of the boosting section is obtained by the third step.
Calculation of boost engine load m fuel:
Directly calculating the loading m fuel of the boosting engine according to the quality factor alpha en of the boosting engine as
mfuel＝αenm0。
Further, obtaining a power parameter estimation value according to the quality parameter estimation value, including:
Estimating the ground thrust P, the mass flow rate m s, the combustion time t b and the engine length L of the boosting engine according to the initial thrust weight ratio k of the input missile, the thrust engine thrust I sp, the propellant density rho of the boosting engine, the filling coefficient Z of the boosting engine, the external diameter D of the missile and the tail section length L p of the boosting engine; the method comprises the following steps:
calculation of the ground thrust P of the boosting engine:
The calculation formula of the ground thrust P of the boosting engine is as follows
P＝km0g0
Wherein the initial thrust-weight ratio k of the missile is known, the missile take-off quality m 0 is obtained in the fourth step, and the sea level gravitational constant g 0 is 9.8m/s;
Calculation of boost engine mass flow rate m s:
the calculation formula of the mass flow rate m s of the boosting engine is as follows
Wherein, the boost engine specific impulse I sp is a known input;
Calculation of the combustion time t b:
The calculation formula of the combustion time t b of the boosting engine is as follows
Calculation of the engine length L:
the propellant volume V is obtained from the propellant density ρ of the booster engine
Wherein the boost engine fill factor Z is a known input;
the sectional area S of the boosting engine is
The length L of the boosting engine can be calculated to be
Wherein the boost engine tail length L p is a known input.
The invention has the following beneficial effects:
(1) According to the method for quickly determining the overall parameters of the boosting and gliding missile, the missile flight trajectory is divided into four sections of the boosting section, the adjusting section, the gliding section and the terminal guidance section for carrying out target trajectory solving, so that the method is more in line with the trajectory flight characteristics of the boosting and gliding missile, and the requirement on target trajectory solving precision is met. The method comprises the following steps: the target trajectory meeting the range requirement is obtained through iterative solution, then a missile overall structure parameter solving method from the target trajectory to trajectory parameters, quality parameters, power parameters and the like is established based on the target trajectory, and the calculation accuracy of the target trajectory directly determines the solving accuracy of the missile overall parameters, so that the method can realize quick, efficient and high-accuracy solving of the boosting and gliding missile overall parameters. The method for quickly determining the overall parameters is mainly applied to the early-stage overall design of the boosting and gliding missile, can quickly calculate the overall parameters such as target trajectory, quality parameters, power parameters and the like through the input of tactical achievement indexes, provides calculation basis and design direction for bullet design, cabin layout, engine model selection and the like in the overall design process of the boosting and gliding missile, and has great reference significance for the overall design of the missile.
(2) According to the method for quickly determining the overall parameters of the boosting and gliding missile, the target trajectory is solved based on the boosting section, the adjusting section, the gliding section and the terminal guidance section, and the vacuum flight hypothesis and the empirical formula are more reasonably used, so that the calculation speed and efficiency are greatly improved on the premise of ensuring a certain solution precision. Because the general parameter of the missile needs to be solved by firstly determining a standard trajectory, the calculation precision of the subsequent general parameter is directly determined by the solving precision of the standard trajectory, if the trajectory of the boosted gliding missile is like a ballistic missile, three-section solving of an active section, a reentry section and a terminal guidance section is adopted, the introduced system error is larger, and the reliability of the calculation result is low; the trajectory is divided into four sections of a boosting section, an adjusting section, a gliding section and a terminal guidance section, so that the method is more in line with the trajectory flight characteristics of the boosting gliding missile, the accuracy of a solving result is higher, and the reference meaning to the overall design is greater.
In addition to the objects, features and advantages described above, the present invention has other objects, features and advantages. The present invention will be described in further detail with reference to the drawings.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the application. In the drawings:
FIG. 1 is a flow chart of a method for quickly determining power parameters of a boosted and gliding missile according to the present invention;
Fig. 2 is a schematic diagram of trajectory segmentation adopted by the rapid determination method of the power parameters of the push-gliding missile of the invention.
Detailed Description
Embodiments of the invention are described in detail below with reference to the attached drawings, but the invention can be implemented in a number of different ways, which are defined and covered by the claims.
Referring to fig. 1 to 2, the invention provides a method for quickly determining overall parameters of a booster and gliding missile, which comprises the following steps:
step one: input missile target range
Inputting the target range of the missile, and dividing the trajectory into a boosting section, an adjusting section, a gliding section and a terminal guidance section; and inputting speed position parameters of each shift point of the trajectory and average lift-drag ratio of the gliding section; the speed and position parameters of each shift point of the trajectory comprise the height of the shutdown point of the boosting section, the height of the vertex of the trajectory and the final speed.
Step two: ballistic parameter estimation
Calculating state parameters of each shift point and the range of each of the boosting section, the adjusting section and the gliding section according to the speed position parameters of each shift point of the trajectory and a preset empirical formula;
The state parameters of each shift point include a shutdown point speed, a speed dip angle, and a ballistic vertex speed.
Step three: judging whether the range requirement is met
Accumulating the ranges of each of the boosting section, the adjusting section, the gliding section and the terminal guidance section to obtain a total range, comparing the total range with a target range, and iteratively solving to ensure that the total range meets the target range requirement and determine a target trajectory;
obtaining a ballistic parameter estimated value according to the target trajectory; the ballistic parameter estimation values comprise a shutdown point speed, a speed dip angle, a ballistic vertex speed and each range.
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 take-off quality and booster engine loading capacity.
Specifically, according to the target trajectory determination in the third step, the shutdown point structure ratio can be obtained, and according to the input quality factors of all parts and the trajectory quality requirements, the quality parameters such as take-off quality, drug loading quantity and the like are calculated.
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 take-off quality and the drug loading in the fourth step, the input initial thrust-weight ratio, specific impulse, fuel density, drug loading coefficient and the like of the boosting engine are utilized to calculate power parameters such as ground thrust, engine combustion time and the like.
The following explains the method for quickly determining the power parameters of the booster and gliding missile by combining the specific embodiments, and specifically comprises the following steps:
Step one: inputting a target range R (400 km), and dividing the trajectory into a boosting section, an adjusting section, a gliding section and a terminal guidance section range according to an empirical formula; inputting the speed and position parameter requirements of each shift point of the trajectory and the average lift-drag ratio of the gliding section; the speed position parameters of each shift point of the trajectory comprise the height of the shutdown point of the boosting section, the height of the vertex of the trajectory and the final speed.
Step two: according to the shift-position speed position input in the step one: the boost segment shutdown point height h 1 (23.8 km), the ballistic vertex height h 2 (45 km), the end velocity v 3 (500 m/s), and the glide segment average lift-drag ratio lambda (2.6) are calculated to obtain a shutdown point velocity v 1 (1603 m/s), a velocity dip angle theta 1 (23.2 °), and a ballistic vertex velocity (i.e., a glide velocity) v 2 (1469 m/s). The injection ranges of each section can be calculated by inputting the specific impulse I sp (2350 Ns/kg) of the boosting engine, and the specific steps are as follows:
S1, calculating the range of the glide segment by an empirical formula to directly obtain the range R 3 of the glide segment as
R3＝0.6R
S2, estimating the slip speed:
by approximating the formula with the range R 3 of the glide segment
Thereby obtaining the slip velocity v 2 as
Wherein, the average lift-drag ratio lambda of the gliding section and the gravitational constant g are 9.8m/s.
S3, estimating the speed of a power-off point of the boosting section
Assuming no energy loss in the adjusting section, the energy conservation formula
Thereby obtaining the shutdown point speed v 1 as
Wherein r 1 is the distance from the shutdown point to the earth center and is obtained by a formula r 1＝h1+r0, r 2 is the distance from the ballistic vertex to the earth center and is obtained by a formula r 2＝h2+r0, and the earth radius r 0 is 6371km.
S4, estimating the speed dip angle of the power-off point of the boosting section
According to the calculation formula of the track eccentricity e and the energy parameter upsilon
υ＝v2r
Thereby obtaining the shutdown point speed inclination angle theta 1 as
S5, estimating the range of the adjustment section
According to kepler equation
r＝a(1-ecosE)
Thereby obtaining a near point angle
Wherein r is the ground center distance, and the semimajor axis a of the elliptical orbit can be defined byAnd obtaining a corresponding close point angle E 1 at the shutdown point and a corresponding close point angle E 2 at the ballistic vertex by substituting the r 1、r2 value.
Thereby obtaining the adjustment range R 2 as
R2＝E2-E1
S6, estimating the range of the boosting section
Assume that the variation rule of the trajectory inclination angle of the boosting section is
Then
Wherein the method comprises the steps of
Wherein, I sp is the ground specific impulse of the boosting engine, h 1 is the height of the shutdown point of the boosting section, and the structural ratio mu k of the shutdown point of the boosting section can be obtained, so that the range R 1 of the boosting section is obtained.
Step three: and a loop iteration step II, namely ending the loop when the designed range meets the target range requirement, and determining a whole-course trajectory scheme (54 km for a booster range, 93km for an adjusting range and 253km for a gliding range). The method comprises the following steps: estimating the total range R' as
R＝R1+R2+R3
And ending the cycle when |R' -R| < epsilon, wherein epsilon is the calculation precision.
The up-range of the boost and gliding missile is mainly borne by the boost section, the adjusting section and the gliding section, and the terminal guidance section occupies a smaller total range, so that the terminal guidance section range can be ignored when the total range is estimated. If it is really necessary to consider the influence of the end-guided range, the input value can be moderately reduced when the target range is input in the step one, and the end-guided range allowance is reserved.
Step four: according to the input glider mass m h (480 kg), the booster engine quality factor alpha en (0.1), the missile tail section quality factor N (0.01) and the booster section shutdown point structure ratio mu k estimated by the trajectory integration module, the quality parameters such as missile take-off mass m 0 (2221 kg), booster engine loading capacity m fuel (1563 kg) and the like are estimated. The method comprises the following steps:
(1) Calculating take-off quality
According to the missile mass formula
m0＝mh+(1-μk)m0+(1-μk)αenm0+Nm0
The available missile take-off mass m 0 is
The mass m h of the gliding mass, the quality factor alpha en of the boosting engine and the quality factor N of the tail section of the missile are all known as inputs, and the shutdown point structure ratio mu k of the boosting section is obtained by the third step.
(2) Calculating the drug loading quantity
Directly calculating the loading m fuel of the boosting engine according to the quality factor alpha en of the boosting engine as
mfuel＝αenm0
Step five: the parameters such as the initial thrust weight ratio k (3.2), the thrust engine thrust I sp (2350 Ns/kg), the propellant density rho (1750 kg/m 3), the loading coefficient Z (0.86) of the thrust engine, the missile outer diameter D (600 mm), the tail section length L p (0.7 m) of the thrust engine, the ground thrust P (69639N) of the thrust engine, the mass flow rate m s (29.6 kg/s), the combustion time t b (52.7 s) and the engine length L (3.67 m) are estimated according to the input missile initial thrust weight ratio k (3.2), the thrust engine thrust I sp (2350 Ns/kg), the loading coefficient Z (0.86) of the thrust engine. The method comprises the following steps:
(1) Estimating ground thrust
The calculation formula of the ground thrust P of the boosting engine is as follows
P＝km0g0
Wherein the initial thrust weight ratio k of the missile is known, the missile take-off mass m 0 is obtained in the fourth step, and the sea level gravitational constant g 0 is 9.8m/s.
(2) Estimating mass flow rate
The calculation formula of the mass flow rate m s of the boosting engine is as follows
Wherein the boost engine specific impulse I sp is a known input.
(3) Estimating combustion time
The calculation formula of the combustion time t b of the boosting engine is as follows
Wherein, the booster engine charge m fuel is obtained in the step four.
(4) Estimating engine length from boost engine propellant density ρ to obtain propellant volume V as
Wherein the boost engine charge factor Z is a known input.
The sectional area S of the boosting engine is
The length L of the boosting engine can be calculated to be
Wherein the boost engine tail length L p is a known input.
In summary, the invention provides a method for quickly determining the overall parameters of a boosting and gliding missile, which solves a target trajectory based on four sections of a boosting section, an adjusting section, a gliding section and a terminal guidance section, and more reasonably uses vacuum flight assumptions and empirical formulas, thereby greatly improving the calculation speed and efficiency on the premise of ensuring a certain solution precision. Because the general parameter of the missile needs to be solved by firstly determining a standard trajectory, the calculation precision of the subsequent general parameter is directly determined by the solving precision of the standard trajectory, if the trajectory of the boosted gliding missile is like a ballistic missile, three-section solving of an active section, a reentry section and a terminal guidance section is adopted, the introduced system error is larger, and the reliability of the calculation result is low; the trajectory is divided into four sections of a boosting section, an adjusting section, a gliding section and a terminal guidance section, so that the method is more in line with the trajectory flight characteristics of the boosting gliding missile, the accuracy of a solving result is higher, and the reference meaning to the overall design is greater.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. 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 and gliding missile is characterized by comprising the following steps of:
Inputting the target range of the missile, and dividing the trajectory into a boosting section, an adjusting section, a gliding section and a terminal guidance section; and inputting speed position parameters of each shift point of the trajectory and average lift-drag ratio of the gliding section; the speed position parameters of each shift point of the trajectory comprise the height of the shutdown point of the boosting section, the height of the vertex of the trajectory and the final speed;
calculating state parameters of each shift point and the range of each of the boosting section, the adjusting section and the gliding section according to the speed position parameters of each shift point of the trajectory and a preset empirical formula; the state parameters of the shift points comprise shutdown point speed, speed dip angle and ballistic vertex speed;
Accumulating the ranges of each of the boosting section, the adjusting section, the gliding section and the terminal guidance section to obtain a total range, comparing the total range with a target range, and iteratively solving to ensure that the total range meets the target range requirement and determine a target trajectory;
obtaining a ballistic parameter estimated value according to the target trajectory; the trajectory parameter estimation value comprises a shutdown point speed, a speed dip angle, a trajectory vertex speed and each range;
obtaining a quality parameter estimation value according to the ballistic parameter estimation value and the ballistic quality requirement;
And obtaining a power parameter estimated value according to the quality parameter estimated value.
2. The method for quickly determining overall parameters of a booster and gliding missile according to claim 1, wherein the speed and position parameters of each shift point of the trajectory, and a preset empirical formula for calculating state parameters of each shift point and ranges of each of the boosting section, the adjusting section and the gliding section, wherein the method comprises the following steps:
According to the input shift-point speed position parameters: the power-off point height h 1, the ballistic vertex height h 2, the tail speed v 3 and the average lift-drag ratio lambda of the gliding section are calculated to obtain the power-off point speed v 1, the speed dip angle theta 1 and the ballistic vertex speed v 2; inputting a specific impulse I sp of the boosting engine, and respectively calculating the range of each section, wherein the specific steps are as follows:
calculation of glide range:
The range R 3 of the glide segment is directly obtained by an empirical formula
R3＝0.6R
Wherein R is the target range;
estimation of slip speed:
by approximating the formula with the range R 3 of the glide segment
Thereby obtaining the slip velocity v 2 as
Wherein, the average lift-drag ratio lambda of the gliding section, the gravitational constant g takes 9.8m/s;
Estimating the speed of a power-off point of a boosting section:
assuming no energy loss in the adjusting section, the energy conservation formula
Thereby obtaining the shutdown point speed v 1 as
Wherein, r 1 is the distance from the shutdown point to the earth center and is obtained by a formula r 1＝h1+r0, r 2 is the distance from the ballistic vertex to the earth center and is obtained by a formula r 2＝h2+r0, and the earth radius r 0 is 6371km;
Estimating the speed and inclination angle of a power-off point of the boosting section:
According to the calculation formula of the track eccentricity e and the energy parameter upsilon
υ＝v2r
Thereby obtaining the shutdown point speed inclination angle theta 1 as
Estimation of the adjustment range:
According to kepler equation
r＝a(1-ecosE)
Thereby obtaining a near point angle
Wherein r is the ground center distance, and the semimajor axis a of the elliptical orbit can be defined byObtaining a corresponding close point angle E 1 at a shutdown point and a corresponding close point angle E 2 at a ballistic vertex by substituting r 1、r2;
Thereby obtaining the adjustment range R 2 as R 2＝E2-E1
Estimation of boost range:
assume that the variation rule of the trajectory inclination angle of the boosting section is
Then
Wherein the method comprises the steps of
Wherein, I sp is the ground specific impulse of the boosting engine, h 1 is the height of the shutdown point of the boosting section, and the structural ratio mu k of the shutdown point of the boosting section can be obtained, so that the range R 1 of the boosting section is obtained.
3. The method for quickly determining the overall parameters of the boosting and gliding missile according to claim 1, wherein the ranges of each of the boosting section, the adjusting section, the gliding section and the terminal guidance section are accumulated to obtain a total range R ', the total range R ' is compared with a target range R, the cycle iteration is carried out, and when |R ' -R| < epsilon, the cycle is ended, the target trajectory is determined, and the target trajectory parameters are obtained; where ε is the accuracy of the calculation.
4. The method for quickly determining overall parameters of a booster and gliding missile according to claim 1, wherein the obtaining of the quality parameter estimation value according to the ballistic parameter estimation value and the ballistic quality requirement includes:
According to the input glide mass m h, the booster engine quality factor alpha en, the missile tail section quality factor N and the booster section shutdown point structure ratio mu k estimated by the trajectory integration module, the missile take-off mass m 0 and the booster engine loading m fuel are estimated, and the specific steps are as follows:
Calculation of missile take-off quality m 0:
According to the missile mass formula
m0＝mh+(1-μk)m0+(1-μk)αenm0+Nm0
The available missile take-off mass m 0 is
Wherein, the mass m h of the gliding mass, the quality factor alpha en of the boosting engine and the quality factor N of the tail section of the missile are all input known, and mu k is the shutdown point structure ratio of the boosting section;
Calculation of boost engine load m fuel:
Directly calculating the loading m fuel of the boosting engine according to the quality factor alpha en of the boosting engine as
mfuel＝αenm0。
5. The method for quickly determining overall parameters of a booster and gliding missile of claim 4, wherein obtaining the power parameter estimate based on the quality parameter estimate comprises:
estimating the ground thrust P, the mass flow rate m s, the combustion time t b and the engine length L of the booster engine according to the initial thrust weight ratio k of the input missile, the booster engine thrust I sp, the booster engine propellant density ρ, the booster engine filling coefficient Z, the missile outer diameter D and the booster engine tail section length L p, wherein the specific steps are as follows:
calculation of the ground thrust P of the boosting engine:
The calculation formula of the ground thrust P of the boosting engine is as follows
P＝km0g0
Wherein, the initial thrust-weight ratio k of the missile is known, m 0 is the missile take-off quality, and the sea level gravitational constant g 0 is 9.8m/s;
Calculation of boost engine mass flow rate m s:
the calculation formula of the mass flow rate m s of the boosting engine is as follows
Wherein, the boost engine specific impulse I sp is a known input;
Calculation of the combustion time t b:
The calculation formula of the combustion time t b of the boosting engine is as follows
Calculation of the engine length L:
the propellant volume V is obtained from the propellant density ρ of the booster engine
Wherein the boost engine fill factor Z is a known input;
the sectional area S of the boosting engine is
The length L of the boosting engine can be calculated to be
Wherein the boost engine tail length L p is a known input.
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