CN201971169U - Miniature attitude orbit control thruster array structure - Google Patents

Abstract

The utility model relates to a miniature attitude orbit control thruster array structure. In order to solve the problem that the existing thruster array is not applied to orbit control, the utility model discloses the thruster array structure of which a basic generating element is a regular hexagon, exists in a circumference form and has central symmetry: in particular arrangement, a first thruster is placed in the center of the basic generating element regular hexagon, and the thrusters are also placed at the six top points of the basic generating element regular hexogen, the side length of the regular hexagon is used as an interval, other thruster positions are derived outwards, and the positions of the other thrusters are required to ensure that the interval between each two thrusters is equal to the side length; and the number of the derived thrusters is determined by the size of the required array scale. The array can avoid the thrust misalignment generated by algorithms, and the coordinate position of each required thruster can be found out fast and accurately through making use of the distribution rules and related control algorithms of the thrusters, therefore, the utilization of the thrusters in the array is improved, and the too early ending of the service life of the array can also be effectively avoided.

Description

A kind of miniature rail control thruster array structure

Technical field

The utility model relates to a kind of miniature rail control thruster array thruster structure.

Background technology

Development and application along with micro-satellite, its high-accuracy posture and track control have also been proposed challenge, need that actuating unit quality and volume are little, integrated level is high, low in energy consumption, reliability is high, small but excellent true momentum can be provided, and miniature solid thruster array can satisfy the requirement of micro-satellite rail control system.The integrated highdensity miniature thruster of miniature solid thruster array energy, each thruster unit produces small momentum, can realize the array mode of lighting a fire arbitrarily, become Thrust Control, the outstanding advantage of this thruster is exactly can be applied to the skin satellite of feather weight or receive on the satellite, is a kind of later-model satellite control engine installation.

Along with various countries are goed deep into gradually to the research of miniature thruster array, press for the application problem that solves array, therefore the research for large scale array becomes present research emphasis.Array structure for present research is regular tetragonal mode, but this kind array is applicable to attitude control is not suitable for track control, when the igniting thruster of needs is odd number, this kind array can't satisfy the requirement that the center with application force overlaps with the satellite barycenter, therefore need be optimized the thruster structure, to be applicable to track control.Therefore need design and both be applicable to attitude control, be applicable to the thruster array structure of track control again.In addition, also be to rarely have research for thruster allocation algorithm based on microthrust device array.

Summary of the invention

The utility model proposes a kind of miniature rail control thruster array structure, improved the problem that is not suitable for track control of existing thruster array.

The basic generator of this thruster array structure is a regular hexagon, exist with the circumference form, has centre symmetry: during concrete layout, place first thruster at the basic orthohexagonal center of generator, thruster is also all placed on basic orthohexagonal six summits of generator, with this orthohexagonal length of side is the interval, outwards expansion derives other thruster position, their position will guarantee all thrusters length of side size for this reason at interval in twos, and the thruster number of deriving is determined by required array scale.Obtaining the thruster characteristics thus is, it is on certain circumference in the center of circle that each thruster all will be distributed in the orthohexagonal center of basic generator; A multiple thruster of 6 is all distributing on each circumference.

On satellite, the thruster array configuration can adopt the form of regular hexahedron, respectively arranges a thruster array on six faces, and is relative in twos, and each is to two degree of freedom of array control.

When thruster need carry out attitude control, adopt the control of three decoupler shafts, three pairs of arrays produce pitching, driftage, rolling moment separately.The specific implementation step is:

Step 1, obtain the moment that need to produce;

Step 2, can provide the situation of moment, carry out moment and decompose, resolve into some execution steps according to required moment and last thruster;

Step 3, the optimum decision sequence of searching, the principle that each sequence step is on cost minimum, the thruster number is minimum makes up, and guarantees each substep required thrust device composition cost minimum, minimum number;

Step 4, store the thruster coordinate in each sequence that solves in the step 3 into control module, control the transmission firing command by control module, and after each thruster uses, its value at cost is made as maxim.

When thruster need carry out track when control, the three pairs of arrays produce separately normal direction, radially, the orbital plane normal thrust.The specific implementation step is:

Step 1, obtain the momentum data that need to produce;

Step 2, be divided into one group, be divided into some groups by this rule for the thruster on each circumference according to 60 ° 6 thrusters of being separated by in twos on the same circumference;

Step 3, the realization of required thrust is divided into some sequences, several of one group of thruster in the grouping of above-mentioned thruster during each sequence makes, what principle that each sequence step is on cost minimum, use group number is minimum and selected thruster made up must make up thruster in the use combination principle on the satellite barycenter with joint efforts;

Step 4, each sequence in the step 3 separated obtain the thruster coordinate and be stored in control module, by the relevant thruster igniting of control module control;

Step 5, after each thruster uses, its value at cost is made as certain fixed value, this fixed value is greater than the maxim of all thrusters combination value at costs.

Beneficial effect

The utility model has designed a kind of miniature rail control thruster array structure, has improved the array area degree of utilization, and can avoid producing because of algorithm the probability of thrust eccentric and reduction mis-ignition; Draw the thruster regularity of distribution in the array, can find out the coordinate position of each thruster fast.And designed the thruster assigning process based on the attitude control of microthrust device array, used algorithm has improved the degree of utilization of thruster in the array, and searches out the thrust available device quickly and accurately.This utility model has also designed the thruster assigning process of the track control of microthrust device array array, and used algorithm is found the solution accurately, and has realized cost minimization, can effectively avoid finishing the array life-span too early, improves the degree of utilization of array.

Description of drawings

Fig. 1 is thruster array distribution figure of the present utility model

Fig. 2 is the grouping scheme drawing of thruster array of the present utility model on coordinate axle

Fig. 3 is the thruster allocation algorithm diagram of circuit of the utility model in attitude control

Fig. 4 is the thruster allocation algorithm diagram of circuit of the utility model in track control

The specific embodiment

Provide this kind thruster array concrete math modeling and algorithm that uses when realizing attitude control and track control below.

This propelling unit array scheme drawing as shown in Figure 1.The basic generator of this thruster array is a regular hexagon, exist with the circumference form, has centre symmetry: during concrete layout, place first thruster at the basic orthohexagonal center of generator, thruster is also all placed on basic orthohexagonal six summits of generator, with this orthohexagonal length of side is the interval, outwards expansion derives other thruster position, their position will guarantee all thrusters length of side size for this reason at interval in twos, and the thruster number of deriving is determined by required array scale.Obtaining the thruster characteristics thus is, it is on certain circumference in the center of circle that each thruster all will be distributed in the orthohexagonal center of basic generator; A multiple thruster of 6 is all distributing on each circumference.

Obtain array coordinate rule by rotation, can obtain thruster coordinate on all circumference, as table 1 example.

0，0

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0.5，0.5a

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1，0

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1，a

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[0028]

Table 1 thruster array distribution rule

On satellite, this thruster array configuration adopts the form of regular hexahedron, respectively arranges a thruster array on six faces, and is relative in twos, and each is to two degree of freedom of array control, as shown in Figure 2

When thruster need carry out attitude control, the specific implementation step was:

Step 1, obtain the moment that need to produce;

Step 2, set up math modeling, ignition problem is converted into one-zero programming problem in the integer programming;

Its mathematical description is as follows:

Objective function:

$\min Z=\underset{k=1}{\overset{K}{\mathrm{\Σ}}}\underset{i=1}{\overset{I}{\mathrm{\Σ}}}\underset{j=1}{\overset{J}{\mathrm{\Σ}}}(u_{(i,j,k)}\×x_{(i,j,k)})---\left(1\right)$

1≤K≤N，1≤I≤N，1≤J≤N

In the formula: min Z represents the cost function of all thruster combinations, make its value minimum; K is the thruster row of being expert at number; I is the row number of thruster column; J is the row number of relative array; N is the array scale, and N is a positive integer, 100 * 100 arrays for example, and if N=100 then is 10 * 10 arrays, then N=10.

Cost function:

$u_{(i,j,k)}={(i-\frac{1+N}{2})}^2+{(j-\frac{1+N}{2})}^2+[{(1-\frac{1+N}{2})}^2+{(N-\frac{1+N}{2})}^2]---\left(2\right)$

Wherein, u _{(i, j, k)}Be the cost function of selected thruster combination, 1≤i≤N, 1≤j≤N, 1≤k≤N constraint condition: $\left\{\begin{array}{c}{K}_c=\left(\underset{k=1}{\overset{K}{\mathrm{\Σ}}}\underset{i=1}{\overset{I}{\mathrm{\Σ}}}\underset{j=1}{\overset{J}{\mathrm{\Σ}}}(F_{\mathrm{eq}}\×L_{\min }\×{|i-j|}_k\×x_{(i,j,k)})\right)\\ x_{(i,j,k)}=\left\{\begin{array}{c}0\\ 1\end{array}\right.\end{array}\right.---\left(3\right)$

Wherein, K _cBe desired moment, L _MinBe two minimum intervals between the thruster, F _EqBe the equivalent thrust of single thruster; When having selected to be positioned at array i row, its relative array j row, during the capable thruster of k, x _{(i, j, k)}=1; Otherwise x _{(i, j, k)}=0.

| i-j| _k* L _MinFor laying respectively at i row and distance two thrusters of j row between, the in fact just arm of force of two the thruster moment that produces of two relative array k on capable.The minimum moment M that array can provide _MinBe:

M _min＝F _eqL _min (4)

Minimum moment can be defined as 1 specific torque.

This model can retrain the control torque that how the thruster unit makes up provides required, with maximization and the minimum purpose of use cost that reaches degree of utilization.Near more then cost function u is more little from array center, preferentially uses the near thruster of decentering, can guarantee that the thruster that stays can provide the thruster array configuration of more generation moment.

Step 3, can provide the situation of moment according to required moment and last thruster, when algorithm is realized, the minimum moment unitization that array can be provided according to formula (4), i.e. 10 expression 10M _Min

With 10 * 10 arrays is example, and the maximum torque that two relative thruster array single files can provide is 9 units, and minimum is 1 unit.With reference to Fig. 1, Fig. 2, with the first behavior example, in the A array first thruster unit can with the moment of 1～9 unit of B array thruster combination results of going together, and the 5th thruster unit be because near apart from center of symmetry, moment that can only 1～5 unit of combination results.For any moment that needs generation, earlier array is searched for the maximum torque that finds each row to produce.

According to the last thruster of required moment and array the situation of moment can be provided, carry out moment and decompose, resolve into some execution steps;

Step 4, the optimum decision sequence of searching, the principle that each sequence step is on cost minimum, the thruster number is minimum makes up, and guarantees each substep required thrust device composition cost minimum, minimum number;

According to the math modeling definition cost function of setting up.

u＝|i-5.5| ²+|j-5.5| ²+40.5 (9)

In the formula: u is the cost that is used for producing a pair of combination of moment; I is the columns of the thruster of lighting a fire in the A array; J is the columns of the thruster of lighting a fire in the B array.

In all possible thruster combined situation, find out the combination of cost minimum, if cost is the same, then select to cut the moment of having found out with required moment then wherein from the group of transverse axis distance, continue to repeat the fwd operation, to the last realize required moment.Seek optimum decision sequence, each sequence step is on cost minimum, and the minimum principle of thruster number makes up, and has guaranteed each substep required thrust device combination cost minimum, minimum number.

The diagram of circuit of this algorithm is as shown in Figure 4:

The moment a that need provide at first is provided, calculate the maximum torque b that each row can provide in the array, judge that whether the moment a that needs is greater than b, if greater than b, just deduct b with required moment a, obtaining provides the thruster of moment b coordinate, with the surplus value that deducts b once more with array in the thrust-drag margin device maximum torque that can provide compare, according to this circulation, less than the maximum torque that array can provide, find out each thruster combination that moment a can be provided up to remaining moment, the cost that compares them, find out the cost minimum, the thruster value at cost that has solved is made as 100, export for all thruster coordinates of having obtained.

This thruster allocation algorithm is because be that branch uses thruster, so can reduce the probability of mis-ignition.

Step 5, store the thruster coordinate in each sequence that solves in the step 4 into control module, control the transmission firing command by control module, and after each thruster uses, its value at cost is made as maxim.

When thruster need carry out track when control, the three pairs of arrays produce separately normal direction, radially, the orbital plane normal thrust.The specific implementation step is:

Step 1, obtain the momentum data that need to produce;

Step 2, be divided into one group, be divided into some groups by this rule for the thruster on each circumference according to 60 ° 6 thrusters of being separated by in twos on the same circumference; As shown in Figure 8, thruster on the thruster array circumference is divided into groups, per 6 thrusters are one group, for thruster number on each circumference is 12 or 18, splits into 2 groups or 3 groups, and the angle that every group of adjacent thruster and array center constitute is 60 degree, therefore has good symmetry, make up when igniting, guarantee easily point of resultant force in array in the heart, every group of brief note is r ₁, r ₂..r _nQueueing discipline is: from the circumference of minimum, increase serial arrangement according to radius of a circle, and for having 2 groups or 3 groups on the same circumference, from the transverse axis positive dirction, the conter clockwise serial arrangement.

Step 3, ignition problem is converted into one-zero programming problem in the integer programming; Its mathematical description is as follows:

Objective function:

$\mathrm{MinZ}=\underset{i=1}{\overset{n}{\mathrm{\Σ}}}(u_i(r_i,X_i)*c_i)$

Cost function:

u _i(r _i，X _i)＝|X _i-0|+|r _i-1|*u _max

Constraint condition:

$I=\underset{i=1}{\overset{n}{\mathrm{\Σ}}}(I_{\min }*\left(m_i\right)*c_i)$

In the formula: MinZ represents the cost function of all thruster combinations, make its value minimum; u _i(r _i, X _i) cost function of the selected thruster of expression combination; r _iRepresent every group sequence number, r _i=1,2 ... .n; m _iExpression thruster quantity; c _iExpression decision variable 0 or 1, X _iThe distance of expression distance center axle Y-axis; u _MaxBe a constant, u _Max=100; I is required momentum; I _MinFor working as a thruster momentum;

Specification of a model:

Objective function is used for the thruster array combination, improves the service life of array, the preferential minimum combination of alternative costs, and the promptly preferential service range array center and the longitudinal axis be apart from minimum, and take the minimum thruster combination of group number; Cost function has been expressed the cost of institute's use thruster; Constraint condition has guaranteed that selected thruster satisfies required momentum requirement.By the comparison of multiple combination results required thrust scheme, can learn that the math modeling of building adheres to specification, omit concrete comparison procedure at this.

Step 4, the realization of required thrust is divided into some sequences, several of one group of thruster in the grouping of above-mentioned thruster during each sequence makes, must thruster being made up in the use combination principle on the satellite barycenter with joint efforts of principle that each sequence step is on cost minimum, use group number is minimum and selected thruster combination;

Algorithm implementation procedure: with the momentum I of single thruster generation _MinBe unit.At first the thruster on each circumference is divided into some groups according to described rule before, every group of 6 thrusters, every group of maximum thrust that can produce is 6I _MinIf required momentum is I, earlier be the momentum that unit produces to be needed with the group, promptly use round (I/6) group thruster earlier, remainder rem (I/6) is produced by the thruster in the less grouping of group number.The selection of each thruster all will be searched in strict accordance with building math modeling, guarantees that use group number is minimum, and thruster distance arrays center and longitudinal axis distance are little.For with thruster its cost being set at 100.

For producing less than 6I _MinMomentum will be handled respectively, as 1 thruster of fruit dot, then needs relative two thruster array combination to produce 2 thrusters of a point, 3 thrusters of a point; As 5 thrusters of fruit dot, then need split into 2 and 3 combination results; Thruster for remainder 1 waste is too many, and therefore, except putting 1 thruster, other remainders calculate according to 7, produces 7I _MinDuring momentum, then be divided into 3I _MinAnd 4I _MinCombination, provide by an array to get final product.

According to the rule of combination of foundation math modeling and definition, the realization of required thrust is divided into some sequences, principle that each sequence step is on cost minimum and self-defining thruster rule of combination make up, and can effectively avoid finishing the array life-span too early.For example, too many if the combination of selected thruster takies the group number, all used the even number thruster in all groups, then can't produce the odd number unit impulse again; If preferentially select distance center distance thruster far away for use, then can reduce the ability that attitude is adjusted.

Diagram of circuit such as Fig. 5 of algorithm show:

The thrust a that will provide at first is provided, every group of maximum that can provide is provided tried hard to recommend b, judge that whether the thrust a that needs is greater than b, if greater than b, if a be 7 then, resolving into 3 and 4 carries out the thruster coordinate and finds the solution, otherwise just deduct b with required thrust a, obtaining provides the thruster of thrust b coordinate, with the surplus value that deducts b once more with array in the thrust-drag margin device maximum thrust that can provide compare, according to this circulation, less than the maximum thrust value that array can provide, find out each thruster combination that thrust a can be provided up to remaining thrust magnitude, the cost that compares them, find out the cost minimum, the thruster value at cost that has solved is made as 100, export for all thruster coordinates of having obtained.

Algorithm simulating is the result show, this algorithm meets the description of math modeling, satisfies the requirement of track control, can improve thruster array service life.

Step 5, each sequence separated obtain the thruster coordinate and be stored in control module, by the relevant thruster igniting of control module control;

Step 6, after each thruster uses, its value at cost is made as certain fixed value, this fixed value is greater than the maxim of all thrusters combination value at costs.

By emulation to the algorithm of control of the attitude of thruster and track control, can find, more than the algorithm that adopted meet the description of corresponding mathematics model, satisfy the requirement that attitude control and track are controlled respectively, can improve thruster array service life.

Claims (3)

1. miniature rail control thruster array structure, it is characterized in that, its basic generator is a regular hexagon, exist with the circumference form, have centre symmetry: during concrete layout, place first thruster at the basic orthohexagonal center of generator, thruster is also all placed on basic orthohexagonal six summits of generator, with this orthohexagonal length of side is the interval, and outwards expansion deriving other thruster position, and their position will guarantee all thrusters length of side size for this reason at interval in twos.

2. a kind of miniature rail control thruster array structure according to claim 1 is characterized in that it is on certain circumference in the center of circle that each thruster all is distributed in the orthohexagonal center of basic generator; A multiple thruster of 6 is all distributing on each circumference.

3. a kind of miniature rail control thruster array structure according to claim 1 is characterized in that, on satellite, this thruster array configuration adopts the form of regular hexahedron, respectively arrange a thruster array on six faces, relative in twos, each is to two degree of freedom of array control.

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