CN104597756B - A kind of great-jump-forward reenters secondary reentry stage voyage predictor method - Google Patents
A kind of great-jump-forward reenters secondary reentry stage voyage predictor method Download PDFInfo
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Abstract
It is as follows that a kind of great-jump-forward reenters secondary reentry stage voyage predictor method: (1) reads in data form; (2) prediction secondary reentry point height h is read in
eI2, speed v
eI2, path angle γ
eI2; (3) prediction secondary reentry point height h is utilized
eI2look into H form, find and h
eI2immediate two height h
iwith h
i+1, record subscripted label i, and calculating K
h=(h
eI2-h
i)/(h
i+1-h
i); (4) prediction secondary reentry point speed v is utilized
eI2look into V form, find and v
eI2immediate two height v
jwith v
j+1, record subscripted label j, and calculating K
v=(v
eI2-v
j)/(v
j+1-v
j); (5) prediction secondary reentry point reentry angle γ is utilized
eI2look into γ form, find and γ
eI2immediate two height γ
kwith γ
k+1, record subscripted label k, and calculating K
γ=(γ
eI2-γ
k)/(γ
k+1-γ
k); (6) utilize record data in conjunction with form L
2(H, V, γ), calculates secondary reentry stage voyage L
p.
Description
Technical field
The present invention relates to a kind of great-jump-forward and reenter secondary reentry stage voyage predictor method, belong to aircraft reentry guidance field.
Background technology
Lunar exploration returns speed reentry aircrafts, and the voyage demand span scope after reentering is 4000---and within 8000km scope, trajectory often exists and significantly rises to process.Owing to reentering the difference of energy level, ballistic characteristics and the Perturbation Effect degree of first reentry stage and secondary reentry stage (or the descending flight stage after energy damping to the first cosmic velocity) have larger difference, therefore the method for guidance of usage forecastings-correction is needed in the high-energy ablated configuration stage, in the suitable scope that ensures to reenter returner energy damping for the first time, provide good reenter original state for secondary reenters.
Under current technical conditions, the computing power of device borne computer is more weak, and needs to complete prediction as early as possible at reentry stage and resolve, thus within the shorter cycle, treats pursuit path upgrade, and ensures guidance closed-loop characteristic.For realizing this target, reentry stage can not directly utilize numerical algorithm to predict 10km parachute-opening point in the early stage, and will select a unique point before parachute-opening point.Then use the method calculated fast, obtain the voyage prediction of the point from unique point to parachute-opening.
In conjunction with the feature of great-jump-forward reentry guidance, after reentering end for the first time, secondary reenters before lift control opens control, and returner keeps zero angle of heel state flight, and trajectory of namely overflowing is the free-flight trajectories of " zero-lift control ".The starting point of this section of trajectory---effusion point, and the terminating point of this section of trajectory---secondary reenters and opens control point, all can as the unique point required.
Because effusion section trajectory is in the edge of rarefied atmosphere, when atmospheric density change, effusion point highly have certain scattered band, if will the section of effusion as unique point, then first need the voyage fast prediction problem solving free flight phasel, basic thinking is state starting point by effusion point, solve two-body problem, and obtain corresponding analytic solution, thus obtain position, the speed of secondary reentry point.But the method have ignored the impact of upper atmosphere and the impact of J2 item Gravitational perturbation, brings certain extrapolation error.Compared with analytic method, utilize numerical prediction to be directly extrapolated to secondary reentry point, unacceptable computation burden can't be brought, therefore the unique point that selected secondary reentry point stops as first reentry stage prediction.And remaining issues is exactly how to utilize the original state of secondary reentry point to obtain drop point voyage forecast fast.
Simple thinking continues to adopt the method for numerical forecasting, is directly extrapolated to parachute-opening point from secondary reentry point, but the problem that the computation burden that described before obviously also existing of the method is overweight.Another one thinking adopts to resolve method of prediction, estimates the voyage of the point from secondary reentry point to parachute-opening.The method can obtain the voyage forecast of outline, but simulation result shows the demand that its estimate accuracy can't meet high precision control completely.For solving above-mentioned two kinds of method Problems existing, need to explore new method.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art part, provides a kind of great-jump-forward to reenter secondary reentry stage voyage predictor method, and when solving numerical computer, expense is large, resolves the problem that forecast precision is relatively low.The method can obtain high secondary reentry stage voyage and estimate, calculate simple, Project Realization is easy simultaneously.
Technical solution of the present invention is: a kind of great-jump-forward reenters secondary reentry stage voyage predictor method, and step is as follows:
(1) possible according to the secondary reentry point of aircraft height span, selects the secondary reentry point height h of aircraft
i, according to order from small to large, be arranged in order and form form H={h
i, i=1,2 ... m, in formula m be more than or equal to 2 positive integer;
(2) possible according to the secondary reentry point of aircraft speed span, selects the secondary reentry point speed v of aircraft
j, according to order from small to large, be arranged in order and form form V={v
j, j=1,2 ... n, n be more than or equal to 2 positive integer;
(3) possible according to the secondary reentry point of aircraft path angle span, selects the secondary reentry point path angle γ of aircraft
k, according to order from small to large, be arranged in order and form form γ={ γ
k, k=1,2 ... p, p be more than or equal to 2 positive integer;
(4) by form H, form V and form γ data be arranged in the form L comprising m × n × p item secondary reentry stage voyage according to one-to-one relationship
2(h
i, v
j, γ
k)={ L
q, q=1,2,3 ..., m × n × p, m × n × p be more than or equal to 8 positive integer, then form L
2in data be:
(5) according to aerial mission, the secondary reentry point height h of the guidance system prediction aircraft of aircraft
eI2, secondary reentry point speed v
eI2, secondary reentry point path angle γ
eI2;
(6) h of comparison step (5)
eI2with the value in form H, if h
eI2>=h
1and h
eI2≤ h
m, find in form H and predict secondary reentry point height h
eI2immediate two secondary reentry point height h
iwith h
i+1, record subscripted label i; According to h
eI2immediate two secondary reentry point height h
iwith h
i+1computed altitude interpolation coefficient K
h, formula is as follows:
K
h＝(h
EI2-h
i)/(h
i+1-h
i)；
If h
eI2<h
1: make height interpolation COEFFICIENT K
h=1, note i=0; If h
eI2>=h
m, make height interpolation COEFFICIENT K
h=0, note i=m;
(7) v of comparison step (5)
eI2with the value in form V, if v
eI2>=v
1and v
eI2≤ v
n, find in form V and predict secondary reentry point speed v
eI2immediate two secondary reentry point speed v
jwith v
j+1, record subscripted label j; According to v
eI2immediate two secondary reentry point speed v
jwith v
j+1computing velocity interpolation coefficient K
v, formula is as follows:
K
v＝(v
EI2-v
j)/(v
j+1-v
j)；
If v
eI2<v
1: make speed interpolation COEFFICIENT K
v=1, note j=0; If v
eI2>=v
n, make speed interpolation COEFFICIENT K
v=0, note j=n;
(8) γ of comparison step (5)
eI2with the value in form γ, if γ
eI2>=γ
1and γ
eI2≤ γ
p, find in form γ and predict secondary reentry point path angle γ
eI2immediate two secondary reentry point path angle γ
kwith γ
k+1, record subscripted label k; According to γ
eI2immediate two secondary reentry point path angle γ
kwith γ
k+1calculating path angle interpolation coefficient K
γ, formula is as follows:
K
γ＝(γ
EI2-γ
k)/(γ
k+1-γ
k)；
If γ
eI2< γ
1: make path angle interpolation coefficient K
γ=1, note k=0; If γ
eI2>=γ
p, make path angle interpolation coefficient K
γ=0, note k=p;
(9) the subscript k that the subscript j that the subscript i recorded according to step (6), step (7) record, step (8) record, from the tables of data L of step (4)
2in get following 8 data and be respectively T
11,t
12,t
13,t
14,t
15,t
16,t
17,t
18:
T
11for form L
2in the value of (k-1) × m × n+ (j-1) × individual data of m+ (i);
T
12for form L
2in the value of (k-1) × m × n+ (j-1) × m+ (i+1) individual data;
T
13for form L
2in the value of the individual data of (k-1) × m × n+ (j) × m+ (i);
T
14for form L
2in the value of (k-1) × m × n+ (j) × m+ (i+1) individual data;
T
15for form L
2in the value of (k) × m × n+ (j-1) × individual data of m+ (i);
T
16for form L
2in the value of (k) × m × n+ (j-1) × m+ (i+1) individual data;
T
17for form L
2in the value of the individual data of (k) × m × n+ (j) × m+ (i);
T
18for form L
2in the value of (k) × m × n+ (j) × m+ (i+1) individual data;
When i is 0, above-mentioned (i) and (i+1) Xiang Jun are taken as 1;
When j is 0, above-mentioned (j-1) and (j) Xiang Jun are taken as 0;
When k is 0, above-mentioned (k-1) and (k) Xiang Jun are taken as 0;
When i is m, above-mentioned (i) and (i+1) Xiang Jun are taken as m;
When j is n, above-mentioned (j-1) and (j) Xiang Jun are taken as n-1;
When k is p, above-mentioned (k-1) and (k) Xiang Jun are taken as p-1;
(10) according to the height interpolation COEFFICIENT K in step (3)
h, to the T in step (9)
11and T
12, carry out interpolation calculation, obtain the first intermediate value T
21, formula is as follows:
T
21＝(1-K
h)×T
11+K
h×T
12；
To the T in step (9)
13and T
14, carry out interpolation calculation, obtain the second intermediate value T
22, formula is as follows:
T
22＝(1-K
h)×T
13+K
h×T
14；
To the T in step (9)
15and T
16, carry out interpolation calculation, obtain the 3rd intermediate value T
23, formula is as follows:
T
23＝(1-K
h)×T
15+K
h×T
16；
To the T in step (9)
17and T
18, carry out interpolation calculation, obtain the 4th intermediate value T
24, formula is as follows:
T
24＝(1-K
h)×T
17+K
h×T
18；
(11) according to the speed interpolation COEFFICIENT K in step (4)
v, to the T in step (10)
21and T
22, carry out interpolation calculation, obtain the 5th intermediate value T
31, formula is as follows:
T
31＝(1-K
v)×T
21+K
v×T
22；
To the T in step (10)
23and T
24, carry out interpolation calculation, obtain the 6th intermediate value T
32, formula is as follows
T
32＝(1-K
v)×T
23+K
v×T
24；
(12) according to the path angle interpolation coefficient K in step (5)
γ, to the T in step (11)
31and T
32, carry out interpolation calculation, obtain secondary reentry stage and estimate voyage L
p, formula is as follows:
L
p＝(1-K
γ)×T
31+K
γ×T
32+L
M；
L in formula
mfor voyage estimates correction factor, usually get 30 ~ 100km.
The present invention's advantage is compared with prior art:
(1) the present invention utilizes priori numerical result to make interpolation calculation form, therefore can provide voyage information of forecasting more accurately.
(2) interpolation calculation of tabling look-up can easily be completed by device borne computer fast, can not cause excessive computation burden.
(3) the own better numerical value stability of linear interpolation method selected of the present invention, the situation simultaneously exceeding form border for independent variable have employed the disposal route of cut-off, there will not be the situation of large deviation.
Accompanying drawing explanation
Fig. 1 is the calculation flow chart of this method;
Fig. 2 adopts the inventive method to carry out calculating the secondary reentry stage prediction voyage deviation obtained;
Fig. 3 is the impact dispersion figure adopting the reentry guidance rule of the inventive method design to realize;
Fig. 4 is the impact dispersion figure adopting the reentry guidance rule of resolving forecasting procedure design to realize.
Embodiment
Below in conjunction with the drawings and specific embodiments, the present invention is described in detail.
As shown in Figure 1, a kind of great-jump-forward reenters secondary reentry stage voyage predictor method, and step is as follows:
(1) possible according to the secondary reentry point of aircraft height span, selects the secondary reentry point height h of aircraft
i, according to order from small to large, be arranged in order and form form H={h
i, i=1,2 ... m, in formula m be more than or equal to 2 positive integer; As got h
1=80km, h
2=85km, h
3=90km, then H={80,85,90};
(2) possible according to the secondary reentry point of aircraft speed span, selects the secondary reentry point speed v of aircraft
j, according to order from small to large, be arranged in order and form form V={v
j, j=1,2 ... n, n be more than or equal to 2 positive integer; As got v
1=7.0km/s, v
2=7.2km/s, v
3=7.4km, then V={7.0,7.2,7.4};
(3) possible according to the secondary reentry point of aircraft path angle span, selects the secondary reentry point path angle γ of aircraft
k, according to order from small to large, be arranged in order and form form γ={ γ
k, k=1,2 ... p, p be more than or equal to 2 positive integer; As got γ
1=-2.0deg, γ
2=-1.2deg, then γ={-2.0,1.2};
(4) by form H, form V and form γ data be arranged in the form L comprising m × n × p item secondary reentry stage voyage according to one-to-one relationship
2(h
i, v
j, γ
k)={ L
q, q=1,2,3 ... m × n × p, m × n × p be more than or equal to 8 positive integer, then form L
2in data be:
L
2,1＝L
2(80,7.0,-2.0)
L
2,2＝L
2(85,7.0,-2.0)
L
2,3＝L
2(90,7.0,-2.0)
L
2,4＝L
2(80,7.2,-2.0)
L
2,5＝L
2(85,7.2,-2.0)
L
2,6＝L
2(90,7.2,-2.0)
L
2,7＝L
2(80,7.4,-2.0)
L
2,8＝L
2(85,7.4,-2.0)
L
2,9＝L
2(90,7.4,-2.0)
L
2,10＝L
2(80,7.0,-1.2)
L
2,11＝L
2(85,7.0,-1.2)
L
2,12＝L
2(90,7.0,-1.2)
L
2,13＝L
2(80,7.2,-1.2)
L
2,14＝L
2(85,7.2,-1.2)
L
2,15＝L
2(90,7.2,-1.2)
L
2,16＝L
2(80,7.4,-1.2)
L
2,17＝L
2(85,7.4,-1.2)
L
2,18＝L
2(90,7.4,-1.2)
(5) according to aerial mission, the secondary reentry point height h of the guidance system prediction aircraft of aircraft
eI2, secondary reentry point speed v
eI2, secondary reentry point path angle γ
eI2; As h
eI2=88, v
eI2=7.14, γ
eI2=-1.8;
(6) h of comparison step (5)
eI2with the value in form H, with h
eI2immediate two secondary reentry point height are h
2with h
3, i=2, accordingly can computed altitude interpolation coefficient K
h=0.6;
(7) v of comparison step (5)
eI2with the value in form V, with v
eI2immediate two secondary reentry point speed are v
1with v
2, j=1; Accordingly can computing velocity interpolation coefficient K
v=0.7;
(8) γ of comparison step (5)
eI2with the value in form γ, with γ
eI2immediate two secondary reentry point path angles are γ
1with γ
2, k=1; Accordingly can calculating path angle interpolation coefficient K
γ=0.25;
(9) the subscript k that the subscript j that the subscript i recorded according to step (6), step (7) record, step (8) record, from the tables of data L of step (4)
2in get following 8 data and be respectively T
11,t
12,t
13,t
14,t
15,t
16,t
17,t
18:
T
11＝L
2,2；
T
12＝L
2,3；
T
13＝L
2,5；
T
14＝L
2,6；
T
15＝L
2,11；
T
16＝L
2,12；
T
17＝L
2,14；
T
18＝L
2,15；
(10) according to the height interpolation COEFFICIENT K in step (3)
h, to the T in step (9)
11and T
12, carry out interpolation calculation, obtain the first intermediate value T
21, formula is as follows:
T
21＝(1-K
h)×T
11+K
h×T
12＝0.4T
11+0.6T
12；
To the T in step (9)
13and T
14, carry out interpolation calculation, obtain the second intermediate value T
22, formula is as follows:
T
22＝(1-K
h)×T
13+K
h×T
14＝0.4T
13+0.6T
14；
To the T in step (9)
15and T
16, carry out interpolation calculation, obtain the 3rd intermediate value T
23, formula is as follows:
T
23＝(1-K
h)×T
15+K
h×T
16＝0.4T
15+0.6T
16；
To the T in step (9)
17and T
18, carry out interpolation calculation, obtain the 4th intermediate value T
24, formula is as follows:
T
24＝(1-K
h)×T
17+K
h×T
18＝0.4T
17+0.6T
18；
Calculated by above-mentioned linear interpolation, the data in step (9) can be utilized to calculate h
eI2during=88km, speed 7.0km/s or 7.2km/s, when path angle-1.0 or-1.2, the estimated value of secondary reentry stage voyage.
(11) according to the speed interpolation COEFFICIENT K in step (4)
v, to the T in step (10)
21and T
22, carry out interpolation calculation, obtain the 5th intermediate value T
31, formula is as follows:
T
31＝(1-K
v)×T
21+K
v×T
22＝0.3T
21+0.7T
22；
To the T in step (10)
23and T
24, carry out interpolation calculation, obtain the 6th intermediate value T
32, formula is as follows
T
32＝(1-K
v)×T
23+K
v×T
24＝0.3T
23+0.7T
24；
Calculated by above-mentioned linear interpolation, the data in step (10) can be utilized to calculate h
eI2during=88km, v
eI2=7.14, when path angle-1.0 or-1.2, the estimated value of secondary reentry stage voyage.
(12) according to the path angle interpolation coefficient K in step (5)
γ, to the T in step (11)
31and T
32, carry out interpolation calculation, obtain secondary reentry stage and estimate voyage L
p, formula is as follows:
L
p＝(1-K
γ)×T
31+K
γ×T
32+L
M＝0.75T
31+0.25T
32+L
M；
L in formula
mfor voyage estimates correction factor, usually get 30 ~ 100km.
Calculated by above-mentioned linear interpolation, the data in step (11) can be utilized to calculate h
eI2during=88km, v
eI2=7.14, γ
eI2when=-1.8, the estimated value of secondary reentry stage voyage.
Above-mentioned algorithm is calculated by linear interpolation, utilizes the data under the differing heights condition that sets in advance, can the simplyst height influence factor be included in final predicting the outcome.Compared with context of methods, in analytical Prediction, highly often utilize earth radius normalization, thousands of meters of magnitude changes of prediction secondary reentry point height, in normalization height, often difference is minimum, want accurate Calculation just to need to retain more significant figure, need to pay certain cost.In addition, adopt high-order interpolation mode if calculated, while the meticulousr result of acquisition, but need to pay more calculated amount.And this method, the object of precision raising can be realized by the method for height table encryption, to device borne computer advantageously.
As shown in Figure 2, utilize said method, get L
mduring=90km, carry out target practice simulating, verifying, obtain the in length and breadth journey scatter diagram of returner at 10km parachute-opening point place as shown in Figure 3.And not adopting method described in this patent, when utilizing the method for resolving forecast to estimate secondary reentry stage voyage, as shown in Figure 4, obvious this patent accompanying method can obtain higher drop point control accuracy to the scatter diagram of journey in length and breadth at 10km parachute-opening point place.
The present invention has returned in exerciser conceptual design at certain and has realized, and method is feasible, and engineering easily realizes, and therefore has practicality.
Claims (2)
1. great-jump-forward reenters a secondary reentry stage voyage predictor method, it is characterized in that step is as follows:
(1) possible according to the secondary reentry point of aircraft height span, selects the secondary reentry point height h of aircraft
i, according to order from small to large, be arranged in order and form form H={h
i, i=1,2 ... m, in formula m be more than or equal to 2 positive integer;
(2) possible according to the secondary reentry point of aircraft speed span, selects the secondary reentry point speed v of aircraft
j, according to order from small to large, be arranged in order and form form V={v
j, j=1,2 ... n, n be more than or equal to 2 positive integer;
(3) possible according to the secondary reentry point of aircraft path angle span, selects the secondary reentry point path angle γ of aircraft
k, according to order from small to large, be arranged in order and form form γ={ γ
k, k=1,2 ... p, p be more than or equal to 2 positive integer;
(4) by form H, form V and form γ data be arranged in the form L comprising m × n × p item secondary reentry stage voyage according to one-to-one relationship
2(h
i, v
j, γ
k)={ L
q, q=1,2,3 ..., m × n × p, m × n × p be more than or equal to 8 positive integer, then form L
2in data be:
L
2,1＝L
2(h
1,v
1,γ
1)
L
2,2＝L
2(h
2,v
1,γ
1)
L
2,mnp＝L
2(h
m,v
n,γ
p)
(5) according to aerial mission, the secondary reentry point height h of the guidance system prediction aircraft of aircraft
eI2, secondary reentry point speed v
eI2, secondary reentry point path angle γ
eI2;
(6) h of comparison step (5)
eI2with the value in form H, if h
eI2>=h
1and h
eI2<h
m, find in form H and predict secondary reentry point height h
eI2immediate two secondary reentry point height h
iwith h
i+1, record subscripted label i; According to h
eI2immediate two secondary reentry point height h
iwith h
i+1computed altitude interpolation coefficient K
h, formula is as follows:
K
h＝(h
EI2-h
i)/(h
i+1-h
i)；
If h
eI2<h
1: make height interpolation COEFFICIENT K
h=1, note i=0; If h
eI2>=h
m, make height interpolation COEFFICIENT K
h=0, note i=m;
(7) v of comparison step (5)
eI2with the value in form V, if v
eI2>=v
1and v
eI2<v
n, find in form V and predict secondary reentry point speed v
eI2immediate two secondary reentry point speed v
jwith v
j+1, record subscripted label j; According to v
eI2immediate two secondary reentry point speed v
jwith v
j+1computing velocity interpolation coefficient K
v, formula is as follows:
K
v＝(v
EI2-v
j)/(v
j+1-v
j)；
If v
eI2<v
1: make speed interpolation COEFFICIENT K
v=1, note j=0; If v
eI2>=v
n, make speed interpolation COEFFICIENT K
v=0, note j=n;
(8) γ of comparison step (5)
eI2with the value in form γ, if γ
eI2>=γ
1and γ
eI2< γ
p, find in form γ and predict secondary reentry point path angle γ
eI2immediate two secondary reentry point path angle γ
kwith γ
k+1, record subscripted label k; According to γ
eI2immediate two secondary reentry point path angle γ
kwith γ
k+1calculating path angle interpolation coefficient K
γ, formula is as follows:
K
γ＝(γ
EI2-γ
k)/(γ
k+1-γ
k)；
If γ
eI2< γ
1: make path angle interpolation coefficient K
γ=1, note k=0; If γ
eI2>=γ
p, make path angle interpolation coefficient K
γ=0, note k=p;
(9) the subscript k that the subscript j that the subscript i recorded according to step (6), step (7) record, step (8) record, from the tables of data L of step (4)
2in get following 8 data and be respectively T
11, T
12, T
13, T
14, T
15, T
16, T
17, T
18:
T
11for form L
2in the value of (k-1) × m × n+ (j-1) × individual data of m+ (i);
T
12for form L
2in the value of (k-1) × m × n+ (j-1) × m+ (i+1) individual data;
T
13for form L
2in the value of the individual data of (k-1) × m × n+ (j) × m+ (i);
T
14for form L
2in the value of (k-1) × m × n+ (j) × m+ (i+1) individual data;
T
15for form L
2in the value of (k) × m × n+ (j-1) × individual data of m+ (i);
T
16for form L
2in the value of (k) × m × n+ (j-1) × m+ (i+1) individual data;
T
17for form L
2in the value of the individual data of (k) × m × n+ (j) × m+ (i);
T
18for form L
2in the value of (k) × m × n+ (j) × m+ (i+1) individual data;
When i is 0, above-mentioned (i) and (i+1) Xiang Jun are taken as 1;
When j is 0, above-mentioned (j-1) and (j) Xiang Jun are taken as 0;
When k is 0, above-mentioned (k-1) and (k) Xiang Jun are taken as 0;
When i is m, above-mentioned (i) and (i+1) Xiang Jun are taken as m;
When j is n, above-mentioned (j-1) and (j) Xiang Jun are taken as n-1;
When k is p, above-mentioned (k-1) and (k) Xiang Jun are taken as p-1;
(10) according to the height interpolation COEFFICIENT K in step (6)
h, to the T in step (9)
11and T
12, carry out interpolation calculation, obtain the first intermediate value T
21, formula is as follows:
T
21＝(1-K
h)×T
11+K
h×T
12；
To the T in step (9)
13and T
14, carry out interpolation calculation, obtain the second intermediate value T
22, formula is as follows:
T
22＝(1-K
h)×T
13+K
h×T
14；
To the T in step (9)
15and T
16, carry out interpolation calculation, obtain the 3rd intermediate value T
23, formula is as follows:
T
23＝(1-K
h)×T
15+K
h×T
16；
To the T in step (9)
17and T
18, carry out interpolation calculation, obtain the 4th intermediate value T
24, formula is as follows:
T
24＝(1-K
h)×T
17+K
h×T
18；
(11) according to the speed interpolation COEFFICIENT K in step (7)
v, to the T in step (10)
21and T
22, carry out interpolation calculation, obtain the 5th intermediate value T
31, formula is as follows:
T
31＝(1-K
v)×T
21+K
v×T
22；
To the T in step (10)
23and T
24, carry out interpolation calculation, obtain the 6th intermediate value T
32, formula is as follows
T
32＝(1-K
v)×T
23+K
v×T
24；
(12) according to the path angle interpolation coefficient K in step (8)
γ, to the T in step (11)
31and T
32, carry out interpolation calculation, obtain secondary reentry stage and estimate voyage L
p, formula is as follows:
L
p＝(1-K
γ)×T
31+K
γ×T
32+L
M；
L in formula
mfor voyage estimates correction factor.
2. a kind of great-jump-forward according to claim 1 reenters secondary reentry stage voyage predictor method, it is characterized in that, voyage estimates correction factor L
mbe 30 ~ 100km.
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