CN1796230A - Method for determining scattered band of exploding fragments of liquid rocket - Google Patents

Abstract

The present invention relates to a method for defining explosive fragment spreading range of liquid rocket. Said method includes the following steps: (1) creating a set of geographic information system suitable for flying navigation area of rocket; (2) creating classification information of rocket explosive fragments; (3), defining the state when the rocket is exploded; (4), defining explosive mode of rocket; (5), defining rocket brisance; (6), defining initial speed of explosive fragment; (7), analyzing explosive fragment force and defining explosive fragment falling points; and (8), defining and displaying spreading range of explosive fragments.

Description

Method for determining scattered band of exploding fragments of liquid rocket

Affiliated technical field

A kind of method of definite scattered band of exploding fragments of liquid rocket, it is the technology of scattering theoretical property and application combination about the explosion of liquid rocket fragment, comprise a cover geographic information system, the method that a kind of definite blast fragment scatters, and insert launch command and control center commander display network and use.The increasing with the propellant consumption of increasing along with satellite (guided missile) launch mission, launching test accidental detonation harmfulness, the fragment that particularly explodes scatters staff and equipment, building is constituted significant threat, and this method provides foundation for the evacuation of the resident launch site near, searching rescue work when accident takes place.

Background technology

For the prediction of liquid propellant rocket scattered band of exploding fragments with determine to have very important safe meaning.All adopt the mode that contracts than experiment to carry out both at home and abroad, the U.S. once repeatedly carrier rocket contract than experiment, domestic also once doing at the CZ-2E/2F rocket contracted than experiment, but contracting of high range is not higher than the experiment confidence level, and only be applicable to the situation of rocket in launch-pad explosion, then can't determine for the situation that rocket aloft explodes.

The content of invention

The method that the purpose of this invention is to provide a kind of definite scattered band of exploding fragments of liquid rocket, fragment distribution situation when domestic various model liquid rockets are blasted in flight course is predicted, for the evacuation of the resident launch site near provides foundation, when blasting accident, determine the scattered band of blast fragment fast, for accident rescue, search site provide foundation.

For achieving the above object, the technical solution used in the present invention is such, promptly a kind of method for determining scattered band of exploding fragments of liquid rocket, and it is characterized in that: method comprises:

(1) set up a cover and the geographic information system that the rocket flight navigating area adapts, comprising:

1., with the landform digitalisation of rocket flight navigating area, set up a cover geographic information system based on city, road, factories and miness, school, the people information of digitized terrain data and rocket flight navigating area;

2., digitized terrain data is mapped in the launching coordinate system any one point (L of corresponding ground _k, B _k, H _k), all can determine its coordinate (x in launching coordinate system _k, y _k, z _k), wherein: L _k, B _k, H _kBe respectively geodetic longitude, geodetic latitude, the earth elevation of certain point on the ground, x _k, y _k, z _kBe respectively this 3 coordinate components in launching coordinate system;

3., receive, handle, write down telemetry data and exterior trajectory measurement data in the rocket flight process;

(2), set up the classified information of rocket blast fragment

According to the fragment that searches after the explosion accident in the past, it is divided into sheet shaped piece, stubby shape fragment, tubulose fragment, irregular shape fragment by its profile and source; Then every kind of fragment is carried out subseries again by its weight, every kind of fragment is measured its area of thrust surface A, quality m respectively _p, density p, drag coefficient C _D, lift coefficient C _L, the angle of attack during flight is stored above information;

State when (3), determining that rocket is blasted

According to the outer course take off data and the telemetry data that receive, determine the speed and the remaining propellant mass of the moment that rocket blasts, residing position, flight;

Parameter is all as the initial condition (IC) of determining rocket blast fragment, wherein:

The moment that the T-blast takes place, unit (s);

X _f, Y _f, Z _fThe location components of rocket in launching coordinate system when-blast takes place, unit (m);

V, V _Xf, V _Yf, V _ZfThe speed of rocket in launching coordinate system and the speed component of 3 coordinate directions when-blast takes place, unit (m/s);

M _1nRemaining conventional propellant quality on rocket when-blast takes place, unit (kg);

M ₁₁Remaining cryogenic propellant quality on rocket when-blast takes place, unit (kg).

(4), determine rocket blast pattern

According to the outer course take off data and the telemetry data that receive, the terrain data in the combining geographic information system is determined the pattern that rocket is blasted, and the needs according to determining the rocket brisance are divided into two kinds of surface shooting and air shootings;

(5), determine the rocket brisance

Brisance represents that with equivalent brisance equals the propellant total amount and multiply by equivalent coefficient, and the equivalent coefficient value is as follows, and when adding uns-dimethylhydrazine and make propellant with dinitrogen tetroxide, surface shooting gets 0.1, and air shooting gets 0.05; Add with liquid hydrogen and to get 0.6 when liquid oxygen is made propellant;

The computing formula of brisance was when air shooting took place:

M _TNT＝M _1n×0.05+M ₁₁×0.6 (I)

The computing formula that ground explosion time brisance takes place is:

M _TNT＝M _1n×0.1+M ₁₁×0.6 (II)

In the formula, M _TNTFor the TNT equivalent of the equivalence of exploding, be amount to be found the solution, M _1nRemaining conventional propellant quality on the rocket when taking place for blast, M ₁₁Remaining cryogenic propellant quality on the rocket when taking place for blast;

After determining brisance, can obtain the parameters of explosion wave, as specific impulse i _s, lateral pressure p _s, be used for determining the accelerating action of shock wave to fragment;

(6), determine the method for blast fragment rate of onset

The speed source that the blast fragment obtains in blast has two, and the firstth, fragment is subjected to the high pressure gas effect and quickens during the propellant tank explosion, and the secondth, explosion wave is to the accelerating action of fragment,

Adopt following formula to determine that fragment is subjected to the high pressure gas effect and the rate of onset that obtains:

$\left\{\begin{array}{c}u=\stackrel{\‾}{U}{\mathrm{ka}}_q\\ \lg \stackrel{\‾}{U}=1.2\lg \stackrel{\‾}{P}+0.91\\ \stackrel{\‾}{P}=\frac{(p-p_0)V_0}{M_C{a}_q^2}\\ k=1.25m_p/m_c+0.375\end{array}\right.---\left(\mathrm{III}\right)$

In the formula (III), u is the speed that fragment obtains, and is the amount that need find the solution, and U, P, k are intermediate variable, a _qFor constant is a velocity of sound in the gas that produces of blast, p is that constant is withstand voltage, the p of propellant tank ₀For constant is bar pressure, the V of blast occurrence positions ₀For constant is volume, the M of propellant tank _cFor constant is quality, the m of propellant tank _pQuality for determined fragment in (2); Following formula (III) can try to achieve that fragment is subjected to the high pressure gas effect and the speed u that obtains;

Adopt following formula to determine that fragment is subjected to the explosion wave effect and the speed that obtains:

$v=\frac{p_0{i}_s{C}_{D}A}{m_p{p}_s}---\left(\mathrm{IV}\right)$

In the formula (IV), v is the fragment speed that the ripple effect obtains that is hit, and is amount, the p that need find the solution ₀For constant is bar pressure, the i of blast occurrence positions _sFor confirmable parameter in (5) is the specific impulse of explosion wave, known.C _DFor confirmable fragment drag coefficient in (2), known; A is determined fragment area of thrust surface in (2); Known.m _pFor determined fragment quality in (2), known; p _sFor confirmable parameter in (5), be the lateral pressure of explosion wave, known; Utilize the above-mentioned equation of known conditions substitution can find the solution that fragment is hit the ripple effect and the speed v that obtains;

Speed u that has determined fragment to be subjected to the high pressure gas effect and obtained and fragment are hit the ripple effect and the speed v that obtains, with blast the flying speed V of rocket constantly take place, the chip velocity V that can throw away to different directions by vector resultant _p, the formula of pressing vector resultant speed is as follows:

${\stackrel{\→}{V}}_p=\stackrel{\→}{V}+\stackrel{\→}{u}+\stackrel{\→}{v}---\left(V\right)$

(7), blast fragment force analysis and drop point are determined method

The blast fragment is carried out force analysis, consider the situation of chip velocity direction on the oxy plane, the interior simultaneous differential equation of listing fragment flight is as follows:

$\left\{\begin{array}{c}\stackrel{\·\·}{X}=-\frac{A{C}_D\mathrm{\ρ}({\stackrel{\·}{X}}^2+{\stackrel{\·}{Y}}^2)}{2m_p}\cos \mathrm{\α}+\frac{{\mathrm{AC}}_L\mathrm{\ρ}({\stackrel{\·}{X}}^2+{\stackrel{\·}{Y}}^2)}{2m_p}\sin \mathrm{\α}\\ \stackrel{\·\·}{Y}=-g-\frac{A{C}_D\mathrm{\ρ}({\stackrel{\·}{X}}^2+{\stackrel{\·}{Y}}^2)}{2m_p}\sin \mathrm{\α}+\frac{A{C}_L\mathrm{\ρ}({\stackrel{\·}{X}}^2+{\stackrel{\·}{Y}}^2)}{2m_p}\cos \mathrm{\α}\end{array}\right.---\left(\mathrm{VI}\right)$

In the set of equations, When flying for fragment at the acceleration/accel of x direction,

When flying for fragment in the speed of x direction, When flying for fragment at the acceleration/accel of y direction,

In the speed of y direction, A is determined fragment area of thrust surface in (2), and is known, C when flying for fragment _DFor confirmable fragment drag coefficient in (2), known; C _LFor confirmable fragment lift coefficient in (2), known, ρ is confirmable fragment density in (2), and is known; m _pFor confirmable fragment quality in (2), known; α is angle of attack when confirmable fragment flies in (2), and is known; Because the initial position (x of back fragment takes place in blast ₀, y ₀, 0) and known, rate of onset

Known, therefore can use solution by iterative method fragment each position (x constantly in-flight _t, y _t, 0), and with geographic information system in terrain data (x _t, y ₁, 0) compare, determine y with method of iteration _t=y ₁The time stop iterative computation, fragment falls earthward, the landing point coordinates of fragment is (x _t, y _t, 0);

For the rate of onset fragment in the oxy plane not, at first determine that according to blast momentary velocity V the angle on itself and xy plane is γ, determine the landing point coordinates (x of fragment then with method of iteration _tCos γ, y _t, x _tSin γ);

(8), determine the scattered band of blast fragment

Determine sheet shaped piece, stubby shape fragment, tubulose fragment, the beginning speed of irregular shape fragment after blast takes place respectively, and carry out velocity resultant by different directions, carry out iterative computation repeatedly and find the solution and write down its drop point, at last the drop point of record is added up, determine the scattered band of blast fragment, in geographic information system, show.

Technique effect

The present invention is owing to described method has following good effect:

(1), the fragment distribution situation when utilizing the present invention to blast in flight course to domestic various model liquid rockets predicts, for the evacuation of the resident launch site near provides foundation;

(2), utilize the present invention can also receive in real time exterior trajectory measurement data and telemetry data in the rocket flight process, when blasting accident, determine the scattered band of blast fragment fast, for accident rescue, search site provide foundation;

(3), utilize definite method of the present invention that the fragment distribution situation of domestic certain twice explosion accident in launch site is predicted that its result and actual conditions are comparatively identical;

(4), to certain model rocket when the theoretical ballistic flight, each flight is launched fragment distribution situation of explosion time constantly and is seen attached list 1.This model rocket in certain emission process in flight when relative 50s blast, its blast fragment distribution situation is seen accompanying drawing 2.

Description of drawings

Accompanying drawing 1 is the diagram of circuit of the inventive method.

Accompanying drawing 2 is domestic certain model rocket flight distribution situation comparison diagram that the actual distribution situation of fragment scattered band and the present invention determine when 50s blasts when relative, among the figure, triangle, oblong and circle marker are the drop point of booster in the actual accidents, satellite, the main remains of rocket, and the rectangular broken line frame is a scattered band of utilizing the inventive method to determine.The result shows that the scope of explosion time fragment scattered band and the inventive method prediction is identical substantially.

Accompanying drawing 3 is when utilizing certain definite model rocket of the inventive method by theoretical ballistic flight, fragment distribution situation synopsis when each flight is blasted constantly.According to this table, just can predict the scope of the fragment distribution in the time of may blasting after this model rocket launching.

The specific embodiment

Embodiment 1 sets up the geographic information system that adapts with the rocket flight navigating area

Adopt 1 high performance graphics workstation as hardware platform, develop supporting with it Geographic Information System (GIS) software, software flow is seen accompanying drawing 1.Use MapGis software to finish the landform digitalisation, use Creator terrain software to generate relief block, use MultiGenvego software to show the terrain information of flight navigating area and city, road, factories and miness, school, the people information of rocket flight navigating area according to digitized terrain data.System is inserted commander's display network of launch command and control center, receive, handle, telemetry data and exterior trajectory measurement data in the storage rocket flight process.

2 pairs of rocket blasts of embodiment fragment is classified

According to the fragment that searches after the blast in the past, it is divided into sheet shaped piece, stubby shape fragment, tubulose fragment, irregular shape fragment by its profile and source.Then to every kind of fragment by its weight be divided into below the 1kg, several below the 10kg, below the 100kg, more than the 100kg, every kind of fragment is measured its drag area, quality, density respectively and is set up rocket blast fragment taxonomy database.

State when embodiment 3 definite rockets are blasted

In the rocket flight process, the outer course take off data and the telemetry data that receive are carried out record, and handle.In blast the back taking place judges the moment that rocket is blasted last effective time according to exterior trajectory measurement data and telemetry data, determine the speed of residing position and flight when rocket is blasted, determine remaining propellant mass in the rocket explosion time tank according to the residual liquid level in the telemetry data.

Embodiment 4 determines the blast pattern of rocket

After blast takes place, cooresponding ground elevation compares among position when the rocket of determining among the embodiment 3 is blasted and the embodiment 1, if the depth displacement of the coordinate of rocket detonation point and corresponding ground coordinate is less than 100m, then determine rocket generation surface shooting, otherwise rocket generation air shooting.

Embodiment 5 determines the brisance of rocket

According to the blast pattern that embodiment 4 determines, the remaining propellant mass that utilizes embodiment 3 to determine uses formula (I) or formula (II) to determine the brisance of rocket, obtains the parameter p of explosion wave then according to brisance _sAnd I _s

Embodiment 6 determines the rate of onset of blast fragment

To all kinds of determining among the embodiment 2, the blast fragment of different quality, the blast impulse wave parameter of using formula (III) and formula (IV) respectively and determining in 5 in conjunction with the embodiments, determine the speed that fragment obtains and the accelerating action of explosion wave in blast, use formula (V) then, the fragment that throws away by the principle subtend different directions of vector resultant carries out velocity resultant, determines the velocity vector of various blast fragments after blast takes place.

Embodiment 7 determines the drop point of blast fragment

To all kinds, different quality, by the blast fragment that different directions throws away, carry out force analysis respectively, and obtain the simultaneous differential equation of shape such as formula (VI).3 initial positions of determining in conjunction with the embodiments then, the rate of onset that embodiment 6 determines with its drop point site of Runge-Kutta method iterative, in the iterative process, judges that its condition that falls earthward is the coordinate components y of fragment in launching coordinate system _tWith the ground point y of this place ₁Coordinate equates.After each iteration finishes, note the coordinate of drop point.

Embodiment 8 determines the scattered band of blast fragment

Each drop point to record among the embodiment 7 is added up, is handled, determine that the blast fragment is to the drop point farthest on 4 directions, it is the maximum range that fragment scatters, and drop point farthest asked arithmetic average, determine the center of fragment scattered band, at last the scattered band of exploding fragments of determining is shown on geographic information system.

Claims (1)

1, a kind of method for determining scattered band of exploding fragments of liquid rocket, it is characterized in that: method comprises:

(1) set up a cover and the geographic information system that the rocket flight navigating area adapts, comprising:

1., with the landform digitalisation of rocket flight navigating area, set up a cover geographic information system based on city, road, factories and miness, school, the people information of digitized terrain data and rocket flight navigating area;

2., digitized terrain data is mapped in the launching coordinate system any one point (L of corresponding ground _k, B _k, H _k), all can determine its coordinate (x in launching coordinate system _k, y _k, z _k), wherein: L _k, B _k, H _kBe respectively geodetic longitude, geodetic latitude, the earth elevation of certain point on the ground, x _k, y _k, z _kBe respectively this 3 coordinate components in launching coordinate system;

3., receive, handle, write down telemetry data and exterior trajectory measurement data in the rocket flight process;

(2), set up the classified information of rocket blast fragment

According to the fragment that searches after the explosion accident in the past, it is divided into sheet shaped piece, stubby shape fragment, tubulose fragment, irregular shape fragment by its profile and source; Then every kind of fragment is carried out subseries again by its weight, every kind of fragment is measured its area of thrust surface A, quality m respectively _p, density p, drag coefficient C _D, lift coefficient C _L, the angle of attack during flight is stored above information;

State when (3), determining that rocket is blasted

According to the outer course take off data and the telemetry data that receive, determine the speed and the remaining propellant mass of the moment that rocket blasts, residing position, flight;

(4), determine rocket blast pattern

According to the outer course take off data and the telemetry data that receive, the terrain data in the combining geographic information system is determined the pattern that rocket is blasted, and the needs according to determining the rocket brisance are divided into two kinds of surface shooting and air shootings;

(5), determine the rocket brisance

Brisance represents that with equivalent brisance equals the propellant total amount and multiply by equivalent coefficient, and the equivalent coefficient value is as follows, and when adding uns-dimethylhydrazine and make propellant with dinitrogen tetroxide, surface shooting gets 0.1, and air shooting gets 0.05; Add with liquid hydrogen and to get 0.6 when liquid oxygen is made propellant;

The computing formula of brisance was when air shooting took place:

M _TNT＝M _ln×0.05+M _ll×0.6 (I)

The computing formula that ground explosion time brisance takes place is:

M _TNT＝M _ln×0.1+M _ll×0.6 (II)

In the formula, M _TNTFor the TNT equivalent of the equivalence of exploding, be amount to be found the solution, M _LnRemaining conventional propellant quality on the rocket when taking place for blast, M _LlRemaining cryogenic propellant quality on the rocket when taking place for blast;

After determining brisance, can obtain the parameters of explosion wave, as specific impulse i _s, lateral pressure p _s, be used for determining the accelerating action of shock wave to fragment;

(6), determine the method for blast fragment rate of onset

The speed source that the blast fragment obtains in blast has two, and the firstth, fragment is subjected to the high pressure gas effect and quickens during the propellant tank explosion, and the secondth, explosion wave is to the accelerating action of fragment,

Adopt following formula to determine that fragment is subjected to the high pressure gas effect and the rate of onset that obtains:

$\left\{\begin{array}{c}u=\stackrel{\‾}{U}k{a}_q\\ \lg \stackrel{\‾}{U}=1.2\lg \stackrel{\‾}{P}+0.91\\ \stackrel{\‾}{P}=\frac{\left({p-p}_0\right)V_0}{M_C{a}_q^2}\\ k=1.25m_p/m_c+0.375\end{array}\right.---\left(\mathrm{III}\right)$

In the formula (III), u is the speed that fragment obtains, and is the amount that need find the solution, and U, P, k are intermediate variable, a _qFor constant is a velocity of sound in the gas that produces of blast, p is that constant is withstand voltage, the p of propellant tank ₀For constant is bar pressure, the V of blast occurrence positions ₀For constant is volume, the M of propellant tank _CFor constant is quality, the m of propellant tank _pQuality for determined fragment in (2); Following formula (III) can try to achieve that fragment is subjected to the high pressure gas effect and the speed u that obtains;

Adopt following formula to determine that fragment is subjected to the explosion wave effect and the speed that obtains:

$v=\frac{p_0{i}_s{C}_{D}A}{m_p{p}_s}---\left(\mathrm{IV}\right)$

In the formula (IV), v is the fragment speed that the ripple effect obtains that is hit, and is amount, the p that need find the solution ₀For constant is bar pressure, the i of blast occurrence positions _sFor confirmable parameter in (5) is the specific impulse of explosion wave, known, C _DFor confirmable fragment drag coefficient in (2), known; A is determined fragment area of thrust surface in (2); Known.m _pFor determined fragment Gu amount in (2), known; p _sFor confirmable parameter in (5), be the lateral pressure of explosion wave, known: as to utilize the above-mentioned equation of known conditions substitution can find the solution that fragment is hit the ripple effect and the speed v that obtains;

Speed u that has determined fragment to be subjected to the high pressure gas effect and obtained and fragment are hit the ripple effect and the speed v that obtains, with blast the flying speed V of rocket constantly take place, the chip velocity V that can throw away to different directions by vector resultant _p, the formula of pressing vector resultant speed is as follows:

${\stackrel{\→}{V}}_p=\stackrel{\→}{V}+\stackrel{\→}{u}+\stackrel{\→}{v}---\left(V\right)$

(7), blast fragment force analysis and drop point are determined method

The blast fragment is carried out force analysis, consider the situation of chip velocity direction on the oxy plane, the interior simultaneous differential equation of listing fragment flight is as follows:

$\left\{\begin{array}{c}\stackrel{\·\·}{X}=-\frac{{\mathrm{AC}}_D\mathrm{\ρ}({\stackrel{\·}{X}}^2+{\stackrel{\·}{Y}}^2)}{2m_p}\mathrm{cas\α}+\frac{{\mathrm{AC}}_L\mathrm{\ρ}({\stackrel{\·}{X}}^2+{\stackrel{\·}{Y}}^2)}{2m_p}\sin \mathrm{\α}\\ \stackrel{\·\·}{Y}=-g-\frac{{\mathrm{AC}}_D\mathrm{\ρ}({\stackrel{\·}{X}}^2+{\stackrel{\·}{Y}}^2)}{{2m}_p}\sin \mathrm{\α}+\frac{{\mathrm{AC}}_L\mathrm{\ρ}({\stackrel{\·}{X}}^2+{\stackrel{\·}{Y}}^2)}{{2m}_p}\cos \mathrm{\α}\end{array}\right.---\left(\mathrm{VI}\right)$

In the set of equations,

When flying for fragment at the acceleration/accel of x direction, When flying for fragment in the speed of x direction, When flying for fragment at the acceleration/accel of y direction,

In the speed of y direction, A is determined fragment area of thrust surface in (2), and is known, C when flying for fragment _DFor confirmable fragment drag coefficient in (2), known; C _LFor confirmable fragment lift coefficient in (2), known, ρ is confirmable fragment density in (2), and is known; m _pFor confirmable fragment quality in (2), known; α is angle of attack when confirmable fragment flies in (2), and is known; Because the initial position (x of back fragment takes place in blast ₀, y ₀, 0) and known, rate of onset Known, therefore can use solution by iterative method fragment each position (x constantly in-flight _t, y _t, 0), and with geographic information system in terrain data (x _t, y _l, 0) compare, determine y with method of iteration _t=y _lThe time stop iterative computation, fragment falls earthward, the landing point coordinates of fragment is (x _t, y _t, 0);

For the rate of onset fragment in the oxy plane not, at first determine that according to blast momentary velocity V the angle on itself and xy plane is γ, determine the landing point coordinates (x of fragment then with method of iteration _tCos γ, y _t, x _tSin γ);

(8), determine the scattered band of blast fragment

Determine sheet shaped piece, stubby shape fragment, tubulose fragment, the beginning speed of irregular shape fragment after blast takes place respectively, and carry out velocity resultant by different directions, carry out iterative computation repeatedly and find the solution and write down its drop point, at last the drop point of record is added up, determine the scattered band of blast fragment, in geographic information system, show.

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