CN104401506A - Zero-counterweight barycenter deploying method for parallel tiling tank satellite - Google Patents
Zero-counterweight barycenter deploying method for parallel tiling tank satellite Download PDFInfo
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- CN104401506A CN104401506A CN201410572356.2A CN201410572356A CN104401506A CN 104401506 A CN104401506 A CN 104401506A CN 201410572356 A CN201410572356 A CN 201410572356A CN 104401506 A CN104401506 A CN 104401506A
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Abstract
The invention provides a zero-counterweight barycenter deploying method for a parallel tiling tank satellite. The method comprises the following steps: (1) preliminarily calculating a satellite barycenter position; (2) preliminarily calculating an adjustable scope of a barycenter; (3) after testing mass characteristics of the satellite, acquiring a measured value of the barycenter, analyzing and calculating the mass and position of a to-be-adjusted propellant according to the measured value, and causing the barycenter to approach to the original point; (4) performing propellant filling for the satellite according to a calculating result of the filling quantity of the propellant of each tank, controlling different filling quantities, and meanwhile, setting a work state after filling. The invention provides the new barycenter deploying method for a parallel tiling tank layout high-orbital satellite; under the condition of not increasing the total mass of the satellite, the original barycenter offset of the satellite is reduced, so that the barycenter variation of a satellite orbital transfer section is reduced, the disturbance torque is reduced, the safety of the satellite orbital transfer is ensured, the consumption of the propellant is reduced, and the service life of the satellite is prolonged.
Description
Technical field
The present invention relates to satellite general technical field, particularly a kind of zero counterweight barycenter concocting method adopting the high rail satellite of tank parallel connection tiling layout.
Background technology
High rail satellite is after the satellite and the rocket are separated, and the general apogee motor firing adopting satellite to carry, after the change rail of several times, arrives planned orbit.In this process, along with the consumption of propellant, centroid of satellite constantly changes, and the thrust of driving engine all the time all through barycenter, therefore can not can produce disturbance torque.The existence of disturbance torque is on the impact of satellite mainly two aspects.Be affect satellite life on the one hand, propellant need be consumed to produce control torque to offset disturbance torque; Be the safety that impact becomes rail on the other hand, cannot produce enough control torques to offset disturbance torque on barycenter change acquires a certain degree clock star, satellite is by out of control.
Become rail section centroid of satellite variable quantity
with the initial centroid position of satellite
there is certain proportionate relationship, meet following formula
Subscript i in above formula represents i-th change rail, proportionality coefficient A
irelevant to the propellant waste of front i change rail and satellite total mass, the change rail strategy taked by concrete satellite model determined.Along with the continuous consumption of propellant, A
icontinuous change is large, usually can reach 0.8-0.9 latter stage at change rail.Visible, the barycenter variable quantity of the bias less change rail section of initial barycenter is less, and therefore, the key controlling disturbance torque is the initial centroid motion reducing satellite.
Usually, the method for installing clump weight on star is adopted to allocate initial barycenter.Satellite mass M is obtained after satellite mass characteristic test
satellitewith initial barycenter
the clump weight of some and quality is installed to reach the object reducing initial barycenter, after making counterweight by ad-hoc location on star
(
for the initial barycenter of the satellite after counterweight), as shown in the formula
I=1 in above formula, 2 ... N represents the quantity of clump weight, M
counterweight ibe the quality of i-th piece of clump weight,
it is the position of i-th piece of clump weight.Satellite mass M
satellitebe made up of two parts, a part is not containing the satellite dry mass M of propellant
dry, another part is the mass M of propellant
push away, there is certain proportionate relationship in this two parts quality.When satellite total mass is unrestricted, after counterweight, satellite dry mass increases
the mass M of propellant
push awayequal proportion increases, then satellite total mass increases; When satellite total mass is limited and when cannot increase, after counterweight, for making total mass constant, must make the mass M of propellant
push awayreduce
namely reduce repropellenting amount, affect satellite service life.
Therefore, adopt the method for installing clump weight to be only applicable to the situation of satellite mass balance abundance, although simple, be the increase in the dry weight of satellite, satellite cannot increase more propellant on the original basis for life-saving.For the satellite of mass balance deficiency, adopt the method for installing clump weight must reduce the adding amount of propellant, affect satellite life.
The lateral dimension of the satellite of tank parallel connection tiling layout is large, easily causes centroid of satellite eccentric; Being discharged by the overbalance of propellant causes the mass distribution of propellant of the same race unbalanced, thus causes the further change of centroid of satellite.Therefore, the barycenter allotment of tank parallel connection tiling layout satellite seems even more important.
At present, domestic high rail satellite does not in-orbit adopt tank parallel connection tiling layout type, adopts tank parallel connection tiling layout, but do not find similar barycenter blending technology or report in multiple satellite models of grinding.
Summary of the invention
For the defect existed in above-mentioned prior art, the invention provides a kind of zero counterweight barycenter concocting method of parallel connection tiling tank satellite, for the high rail satellite adopting tank parallel connection tiling layout, propose a kind of not by zero counterweight barycenter concocting method of satellite total mass restriction, reduce to become the barycenter variable quantity of rail section and corresponding disturbance torque, thus guarantee the safety becoming rail.The present invention is controlled by the adding amount of the propellant to each tank, reaches the object of adjustment centroid of satellite.
For achieving the above object, the technical solution adopted in the present invention is as follows:
A zero counterweight barycenter concocting method of tiling tank satellite in parallel, comprises step as follows:
(1) budget centroid of satellite position;
(2) the adjustable scope of budget barycenter;
(3) after the mass property test of satellite, obtain the measured value of barycenter, according to measured value, analyze and calculate the propellant mass and position that need adjust, making barycenter close toward initial point;
(4) according to the repropellenting amount result of calculation of each tank, implement the repropellenting of satellite, control different adding amounts, meanwhile, the mode of operation after filling is set.
The concrete steps of the initial barycenter adjustable range of described (2) step budget satellite are as follows:
A) biggest quality difference of budget propellant tank filling of the same race propellant
Oxidizer tank filling biggest quality discrepancy delta M
oxygenbudget is as follows:
In above formula, β is the maximum fullness coefficient of tank, ρ
oxygenfor oxidizer density, V
storagefor tank volume, H is the ratio of oxidizer density and fuel density, M
push awayfor propellant mass;
Fuel tank filling biggest quality discrepancy delta M
combustionbudget is as follows:
ρ in above formula
combustionfor fuel density p
combustion=ρ
oxygen/ H;
B) budget X to adjustable range
X is to adjustable range | and Δ X| budget is as follows:
M
satellitefor satellite quality, r is the radius of circle of tank distribution, and α is that the line of oxidizer tank and the angle of X-axis are arrived in the center of circle;
C) adjustable range of budget Y-direction
Y-direction adjustable range | Δ Y| budget is as follows:
The concrete steps of described (3) step are as follows:
A) the propellant kind that need adjust and tank position is tentatively judged
According to actual measurement barycenter place quadrant and position, judge qualitatively the propellant kind that need adjust and tank position, obtain which tank and add note, which tank is annotated less;
B) just noly at last designing requirement can be reached
According to the budget result of adjustable range of the centroid position of actual measurement and X, Y-direction, whether the barycenter after primary Calculation adjustment can reach designing requirement, if actual measurement barycenter meets design requirement, then each tank only need balance filling; After carrying out barycenter allotment according to the method for zero counterweight, can meet design requirement, then carry out the work of next step;
C) final barycenter allotment target is determined
In conjunction with actual measurement barycenter and designing requirement, determine final barycenter allotment target
the principle set objectives meets design requirement while being minimizing adjustment amount and leaves certain surplus;
D) each tank adding amount is calculated
After above-mentioned conditions being possessed, first can calculate the actual mass discrepancy delta M of propellant tank of the same race
oxygen is realwith Δ M
combustion is real, both meet following relation respectively at X and Y-direction:
In above formula
with
be respectively
at the component of X and Y-direction,
represent the measured value of centroid of satellite position,
with
be respectively
at the component of X and Y-direction, Δ M
oxygen is realrepresent the actual mass difference of oxidizer, Δ M
combustion is realrepresent the actual mass difference of fuel; Δ M
oxygen is real>0 and Δ M
combustion is real>0, represents in the tank of propellant of the same race and adds note near the tank of satellite+X side, separate above-mentioned linear equation in two unknowns group, can obtain:
The adding amount of each tank is respectively:
M
oxygen A is real=M
oxygen A+ 0.5 Δ M
oxygen is real
M
oxygen B is real=M
oxygen B-0.5 Δ M
oxygen is real
M
combustion A is real=M
combustion A+ 0.5 Δ M
combustion is real
M
combustion B is real=M
combustion B-0.5 Δ M
combustion is real
M
oxygen A, M
oxygen B, M
combustion A, M
combustion Baccording to the propellant mass of uniform mode in oxidizer tank A, oxidizer tank B, fuel tank A and fuel tank B respectively, wherein M
oxygen A=M
oxygen B, M
combustion A=M
combustion B, M
oxygen A+ M
oxygen B+ M
combustion A+ M
combustion B=M
push away,m
push awayfor the propellant total mass that satellite need be annotated.
Described (4) step, arranges the mode of operation after filling and comprises:
During becoming rail, keep the difference of repropellenting amount;
After change rail terminates, residual propellant need be guaranteed all in the management devices of tank;
During operation on orbit, carry out tonifying Qi by the tank many to Residual Propellant, the propellant content in propellant tank of the same race is tended to balance, or by first using the propellant in the many tank of Residual Propellant, propellant content is tended to balance.
Zero counterweight barycenter concocting method provided by the present invention, compared with existing ballasting method, has following beneficial effect:
(1) do not re-use traditional clump weight and balance annotation method, realize the adjustment of centroid of satellite, reduce the barycenter variable quantity becoming rail section, reduce the side-play amount of the initial barycenter of satellite, thus reduce the disturbance torque becoming rail section, ensure the safety of Satellite Orbit Maneuver;
(2) when satellite mass balance deficiency, clump weight cannot be adopted to allocate centroid of satellite, the inventive method does not increase propellant mass, does not increase satellite total mass, can realize the allotment of barycenter;
(3) replacing existing clump weight, when not increasing satellite total mass, reaching the effect of counterweight, the actual effect serving saving propellant.
(4) by the independent repropellenting amount controlled in each tank, the centroid position of adjustment satellite.
(5) centroid of satellite of tank parallel connection tiling layout can adjust arbitrarily in the certain limit of transverse direction.
Accompanying drawing explanation
By reading the detailed description done non-limiting example with reference to the following drawings, other features, objects and advantages of the present invention will become more obvious:
Fig. 1 is the schematic layout pattern of tiling tank one embodiment in parallel;
Fig. 2 is the birds-eye view of Fig. 1.
Detailed description of the invention
Below in conjunction with main flow " four tanks parallel connection tiling layouts bipropellant propulsion systems " for example, the present invention is described in detail.Following examples will contribute to those skilled in the art and understand the present invention further, but not limit the present invention in any form.It should be pointed out that the present invention is not limited to above-mentioned particular implementation, the present invention is applicable to " propulsion system of tank tiling ", there is ubiquity, to those skilled in the art, without departing from the inventive concept of the premise, some distortion and improvement can also be made.These all belong to protection scope of the present invention.
Shown in Fig. 1, Fig. 2, the parallel connection tiling tank layout of certain satellite provided by the present invention, this design of satellites mass M
satellite=5300kg, its Satellite dry mass M
dry=2250kg, propellant mass M
push away=3050kg, has propellant tank (the position A of two oxidizer tanks of four 704L capacity
1and B
1expression, two fuel tank position A
2and B
2represent), be symmetrically distributed on circle that radius is r=960mm.Wherein, layout is at+X+Y and-X-Y quadrant respectively for oxidizer tank A and B, and fuel tank A and B difference layout is at+X-Y and-X+Y quadrant; Propellant tank of the same race about origin symmetry, different propellant tank about rotational symmetry, OA
1be α=30 ° with the angle of OX, the rest may be inferred for all the other.
The placement position of tank is different, and its X for satellite is to different with the barycenter influence degree of Y-direction.When α is less than 45 °, on satellite X to barycenter impact larger; When α is greater than 45 °, larger on the barycenter impact of satellite Y-direction.Density due to oxidizer is greater than fuel (ratio is H=1.65), and therefore, the adjustment to centroid of satellite implemented by preferential use oxidizer, also can use oxidizer and the adjustment of fuel enforcement to centroid of satellite according to actual conditions simultaneously.
The idiographic flow of the present invention zero counterweight barycenter concocting method is as follows:
(1) budget centroid of satellite position
In the design process of satellite, should using initial for satellite centroid position at initial point as design objective, and according to the design point of satellite, the initial centroid position of budget satellite, makes the control errors of itself and measured value within the specific limits.
(2) the adjustable scope of budget barycenter
Due to the difference of each satellite model, quantity and the volume of the total mass of satellite, propellant mass, tank are all variant.In the design process of satellite, according to the design point of satellite, the adjustment capability of this zero counterweight barycenter concocting method need be considered.The present embodiment is for the bipropellant propulsion system of four tank parallel connection tiling layouts, and the concrete steps of the initial barycenter adjustable range of budget satellite are as follows:
A) biggest quality difference of budget propellant tank filling of the same race propellant
Oxidizer tank filling biggest quality discrepancy delta M
oxygenbudget is as follows:
In above formula, β is the maximum fullness coefficient (being herein 95%) of tank, ρ
oxygenfor oxidizer density (is 1.458g/cm herein
3(when 15 DEG C)), V
storagefor tank volume (being 704L) herein, then Δ M
oxygen=51kg.
Fuel tank filling biggest quality discrepancy delta M
oxygenbudget is as follows:
ρ in above formula
combustionfor fuel density (ρ
combustion=ρ
oxygen/ H), then Δ M
combustion=31kg.
B) budget X to adjustable range
X is to adjustable range | and Δ X| budget is as follows:
After substituting into each value, | Δ X|=12.9mm.
C) adjustable range of budget Y-direction
Y-direction adjustable range | Δ Y| budget is as follows:
After substituting into each value, | Δ Y|=7.4mm.
(3) analyze and calculate the propellant mass and position that need adjust
After the mass property test of satellite, obtain the measured value of barycenter
according to measured value, analyze and calculate the propellant mass and position that need adjust, make barycenter close toward initial point, concrete steps are as follows:
A) the propellant kind that need adjust and tank position is tentatively judged
According to actual measurement barycenter place quadrant and position, judge qualitatively the propellant kind that need adjust and tank position, obtain which tank and add note, which tank is annotated less.
B) just noly at last designing requirement can be reached
According to the budget result of adjustable range of the centroid position of actual measurement and X, Y-direction, whether the barycenter after primary Calculation adjustment can reach designing requirement.If actual measurement barycenter meets design requirement, then each tank only need balance filling; After carrying out barycenter allotment according to the method for zero counterweight, can meet design requirement, then carry out the work of next step; After carrying out barycenter allotment according to the method for zero counterweight, still can not meet design requirement, then need to adopt other measures.
C) final barycenter allotment target is determined
In conjunction with actual measurement barycenter and designing requirement, determine final barycenter allotment target
the rule set objectives meets design requirement while being minimizing adjustment amount and leaves certain surplus.
D) each tank adding amount is calculated
After above-mentioned conditions being possessed, first can calculate the actual mass discrepancy delta M of propellant tank of the same race
oxygen is realwith Δ M
combustion is real, both meet following relation respectively at X and Y-direction:
In above formula
with
be respectively
at the component of X and Y-direction,
with
for being respectively
at the component of X and Y-direction, Δ M
oxygen is real>0 and Δ M
combustion is realthe implication of >0 is add note near the tank of satellite+X side in the tank of propellant of the same race.Separate above-mentioned linear equation in two unknowns group, can obtain:
The adding amount of each tank is respectively:
M
oxygen A is real=M
oxygen A+ 0.5 Δ M
oxygen is real
M
oxygen B is real=M
oxygen B-0.5 Δ M
oxygen is real
M
combustion A is real=M
combustion A+ 0.5 Δ M
combustion is real
M
combustion B is real=M
combustion B-0.5 Δ M
combustion is real
When
time, solve
then the adding amount of each tank is respectively M
oxygen A is real=965.8kg, M
oxygen B is real=933.3kg, M
combustion A is real=575.2kg, M
combustion B is real=575.8kg.
(4) repropellenting and subsequent operating state are arranged
According to the repropellenting amount result of calculation of each tank, implement the repropellenting of satellite, control different adding amounts.After filling, relative set is carried out to propulsion system state, guarantee the difference keeping repropellenting amount before Satellite Orbit Maneuver between different tank.During becoming rail, keep the difference of repropellenting amount.After change rail terminates, residual propellant need be guaranteed all in the management devices of tank.During operation on orbit, carry out tonifying Qi by the tank many to Residual Propellant, the propellant content in propellant tank of the same race tended to balance, also by first use Residual Propellant many tank in propellant, propellant content is tended to balance.
Above specific embodiments of the invention are described.It will be appreciated that, the present invention is not limited to above-mentioned particular implementation, and the present invention is applicable to " propulsion system of tank tiling ", has ubiquity, those skilled in the art can make various distortion or amendment within the scope of the claims, and this does not affect flesh and blood of the present invention.
Claims (4)
1. a zero counterweight barycenter concocting method of tiling tank satellite in parallel, is characterized in that, comprise step as follows:
(1) budget centroid of satellite position;
(2) the adjustable scope of budget barycenter;
(3) after the mass property test of satellite, obtain the measured value of barycenter, according to measured value, analyze and calculate the propellant mass and position that need adjust, making barycenter close toward initial point;
(4) according to the repropellenting amount result of calculation of each tank, implement the repropellenting of satellite, control different adding amounts, meanwhile, the mode of operation after filling is set.
2. zero counterweight barycenter concocting method of parallel connection tiling tank satellite according to claim 1, it is characterized in that, the concrete steps of the initial barycenter adjustable range of described (2) step budget satellite are as follows:
A) biggest quality difference of budget propellant tank filling of the same race propellant
Oxidizer tank filling biggest quality discrepancy delta M
oxygenbudget is as follows:
In above formula, β is the maximum fullness coefficient of oxidizer tank, ρ
oxygenfor oxidizer density, V
storagefor tank volume, H is the ratio of oxidizer density and fuel density, M
push awayfor propellant total mass;
Fuel tank filling biggest quality difference M Δ
combustionbudget is as follows:
ρ in above formula
combustionfor fuel density p
combustion=ρ
oxygen/ H;
B) budget X to adjustable range
X is to adjustable range | and Δ X| budget is as follows:
M
satellitefor satellite quality, r is the radius of circle of tank distribution, and α is that the line of oxidizer tank and the angle of X-axis are arrived in the center of circle;
C) adjustable range of budget Y-direction
Y-direction adjustable range | Δ Y| budget is as follows:
3. zero counterweight barycenter concocting method of parallel connection tiling tank satellite according to claim 2, it is characterized in that, the concrete steps of described (3) step are as follows:
A) the propellant kind that need adjust and tank position is tentatively judged
According to actual measurement barycenter place quadrant and position, judge qualitatively the propellant kind that need adjust and tank position, obtain which tank and add note, which tank is annotated less;
B) just noly at last designing requirement can be reached
According to the budget result of adjustable range of the centroid position of actual measurement and X, Y-direction, whether the barycenter after primary Calculation adjustment can reach designing requirement, if actual measurement barycenter meets design requirement, then each tank only need balance filling; After carrying out barycenter allotment according to the method for zero counterweight, can meet design requirement, then carry out the work of next step;
C) final barycenter allotment target is determined
In conjunction with actual measurement barycenter and designing requirement, determine final barycenter allotment target
the principle set objectives meets design requirement while being minimizing adjustment amount and leaves certain surplus;
D) each tank adding amount is calculated
After above-mentioned conditions being possessed, first can calculate the actual mass discrepancy delta M of propellant tank of the same race
oxygen is realwith Δ M
combustion is real, both meet following relation respectively at X and Y-direction:
In above formula
with
be respectively
at the component of X and Y-direction,
represent the measured value of centroid of satellite position,
with
be respectively
at the component of X and Y-direction, Δ M
oxygen is realrepresent the actual mass difference of oxidizer, Δ M
combustion is realrepresent the actual mass difference of fuel; Δ M
oxygen is real>0 and Δ M
combustion is real>0, represents in the tank of propellant of the same race and adds note near the tank of satellite+X side, separate above-mentioned linear equation in two unknowns group, can obtain:
The adding amount of each tank is respectively:
M
oxygen A is real=M
oxygen A+ 0.5 Δ M
oxygen is real
M
oxygen B is real=M
oxygen B-0.5 Δ M
oxygen is real
M
combustion A is real=M
combustion A+ 0.5 Δ M
combustion is real
M
combustion B is real=M
combustion B-0.5 Δ M
combustion is real
M
oxygen A, M
oxygen B, M
combustion A, M
combustion Baccording to the propellant mass of uniform mode in oxidizer tank A, oxidizer tank B, fuel tank A and fuel tank B respectively, wherein M
oxygen A=M
oxygen B, M
combustion A=M
combustion B, M
oxygen A+ M
oxygen B+ M
combustion A+ M
combustion B=M
push away, M
push awayfor the propellant total mass that satellite need be annotated.
4. zero counterweight barycenter concocting method of parallel connection tiling tank satellite according to claim 1, is characterized in that described (4) step arranges the mode of operation after filling and comprises: during becoming rail, keeps the difference of repropellenting amount; After change rail terminates, residual propellant need be guaranteed all in the management devices of tank; During operation on orbit, carry out tonifying Qi by the tank many to Residual Propellant, the propellant content in propellant tank of the same race is tended to balance, or by first using the propellant in the many tank of Residual Propellant, propellant content is tended to balance.
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| CN104401506B CN104401506B (en) | 2017-01-04 |
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