A method and device for designing energy storage for aircraft

Abstract

The present invention relates to the technical field of aircraft energy storage device design, and specifically, to an aircraft energy storage design method and device. The method includes obtaining energy demand parameters of an aircraft energy storage device based on the aircraft's electrical energy demand for the aircraft energy storage device. Based on the obtained energy demand parameters, battery performance parameters, capacitor performance parameters, battery converter performance parameters, and capacitor converter performance parameters of different models are obtained. Based on battery performance parameters, capacitor performance parameters, battery converter performance parameters, capacitor converter performance parameters, and energy demand parameters of different models, an energy storage combination M is obtained. Based on the energy storage combination M and the energy demand parameters, battery performance parameters, capacitor performance parameters, battery converter performance parameters, and capacitor converter performance parameters, a design scheme with the smallest corresponding energy storage weight among all mi is obtained. This solves the problem of how to quickly design a lightweight aircraft energy storage device.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft energy storage device design, and in particular to an aircraft energy storage design method and device. Background Art

[0002] With the rapid development of aircraft, the demand for energy storage devices has greatly increased, mainly because the flight envelope of aircraft is gradually expanding, and the operating state of the generator is difficult to guarantee, especially in the process of mode switching from turbine mode to ramjet mode of the engine, the upper limit of the power that the main generator can provide will drop for a short time, and the energy storage device needs to be put into operation to fill the power gap; secondly, the short-term high-power loads (such as high-power radar, pulse weapons, etc.) loaded on the aircraft will cause the peak-to-average ratio of the aircraft's power demand curve to increase significantly. If the peak power demand is met by increasing the generator capacity, it will not only greatly increase the size, weight and design difficulty of the generator, but also make the generator work in an unsaturated state for a long time, affecting its efficiency and service life. The energy storage device can better solve this problem and meet the peak power demand in the form of "peak shaving and valley filling"; thirdly, in order to save fuel, the aircraft will be in an unpowered taxiing state during the return phase, that is, the engine is turned off to slow down the aircraft. During this process, the aircraft's onboard system still has a demand for electricity, and the energy storage device is also needed to provide energy.

[0003] Therefore, in the design process of the aircraft, the design of the aircraft energy storage device will be an indispensable part. However, in the design process, faced with a large number of batteries and capacitors of various types, how to use the existing batteries and capacitors in series or parallel to quickly design a design that meets the aircraft's power requirements and lightweight requirements for the energy storage device has become an urgent problem that needs to be solved. Summary of the invention

[0004] In order to solve the problem of how to quickly design a lightweight aircraft energy storage device, the present invention provides an aircraft energy storage design method and device.

[0005] In a first aspect, the present invention provides an aircraft energy storage design method, the aircraft energy storage design method comprising:

[0006] Step S10, based on the electric energy demand of the aircraft for the aircraft energy storage device, obtaining energy demand parameters of the aircraft energy storage device;

[0007] Step S20, based on the energy demand parameter obtained, obtaining battery performance parameters of different models, capacitor performance parameters of different models, battery converter performance parameters of different models, and capacitor converter performance parameters of different models;

[0008] Step S30, based on the battery performance parameters of different models, the capacitor performance parameters of different models, the battery converter performance parameters of different models, the capacitor converter performance parameters of different models and the energy demand parameters, obtain the energy storage combination M={m i |1≤i},m i =(X k , Y j , A a , B b ); wherein, the m i Includes various battery pack models X k , various types of capacitor banks Y j 、Various types of battery converters A a , various types of capacitor converters B b ; 1≤k≤n1, 1≤j≤n2, 1≤a≤n3, 1≤b≤n4; n1, n2, n3, n4 are all natural numbers greater than 2; the battery pack X k comprising a plurality of batteries of the same type; the capacitor group Y j Including multiple capacitors of the same model;

[0009] Step S40, based on the energy storage combination M and the energy demand parameter, the battery performance parameter, the capacitor performance parameter, the battery converter performance parameter, and the capacitor converter performance parameter, obtain all m i The design scheme with the smallest energy storage weight corresponding to the design scheme; wherein the design scheme includes the number of battery packs connected in series N BS 、N number of battery packs in parallel BP 、N number of capacitors in series CS 、N number of capacitors in parallel CP ; The energy storage weight includes the battery pack weight M x 、Capacitor bank weight M y 、Battery converter weight M k1 、Capacitor converter weight M k2 sum.

[0010] In some embodiments, the energy demand parameter in step S10 includes an instantaneous maximum power demand P S , Instantaneous power duration T S , long-term maximum power demand P C , Long-term power duration T C ;P S Greater than P C ; T S Less than T C .

[0011] In some embodiments, the aircraft energy storage design method further includes:

[0012] Step S11: based on the energy demand of the aircraft, obtain the first electrical equipment parameter W of the aircraft a =(P n , T n ); where P n is the power of the first electrical equipment, T n P n The corresponding working time of the first electrical equipment; 2≤n≤N, where N is the number of electrical equipment;

[0013] Step S12: based on the first electrical equipment parameter W a , obtain the instantaneous maximum power demand P S =MAX(P n ), the instantaneous power duration T S P S The corresponding working hours of electrical equipment.

[0014] In some embodiments, the aircraft energy storage design method further includes:

[0015] Step S13: based on the first electrical equipment parameter W a and the instantaneous maximum power demand P S , obtain the second electrical equipment parameter W of the aircraft b =(P m , T m ); where W b W a Remove MAX (P n ) after the parameter, P m is the power of the second electrical equipment, T m P m The corresponding working time of the second electrical equipment; 1≤m≤N-1;

[0016] Step S14: based on the second electrical equipment parameter W b , obtain the long-term maximum power demand P C =MAX(P m ), the long-term power duration T C =Q / P C ; Where Q is the maximum long-term energy demand; .

[0017] In some embodiments, the battery performance parameter in step S20 includes the battery voltage U B 、Battery capacity Q B , battery discharge rate C, battery weight M B ; The capacitor performance parameters include capacitor voltage U C 、Capacitance Q C、Capacitor weight M C The battery converter performance parameters include the low voltage side voltage lower limit U a1min , Low voltage side voltage upper limit U a1max , Rated power P wa 、The battery converter weight M ka ;P C ≤P wa The performance parameters of the capacitor converter include the lower limit of the low voltage side voltage U a2min , Low voltage side voltage upper limit U a2max , Rated power P wb , the weight of the capacitor converter M kb ;P S -P C ≤P wb .

[0018] In some embodiments, step S40 includes:

[0019] Step S41, based on the energy storage combination M and the energy demand parameter, the battery performance parameter, the capacitor performance parameter, and the converter performance parameter, i The battery pack X k Set a U BZ The initial value of an m i The capacitor group Y j Set a U CZ The initial value of BZ is the voltage of the battery pack; U a1min ≤U BZ ≤U a1max ; U CZ is the voltage of the capacitor bank; U a2min ≤U CZ ≤U a2max ;

[0020] Step S42, based on an m i Set a U BZ The initial value and U CZ The initial value of the battery pack is obtained by obtaining a corresponding design scheme; wherein the design scheme includes the number of battery packs in series N BS , the number of parallel connected battery packs N BP The number of capacitors connected in series is N CS , the number of capacitor groups connected in parallel N CP ;

[0021] Step S43, based on the m i A corresponding design scheme is to adjust U according to the first interval threshold s1. BZ , adjust U according to the second interval threshold s2 CZTo obtain the m i The remaining corresponding design schemes; 0<s1≤U a1max -U a1min ; 0<s2≤U a2max -U a2min ;

[0022] Step S44, based on the m i The corresponding design solution group obtains the m i The design scheme with the smallest energy storage weight in the corresponding design scheme group; wherein the design scheme group includes multiple design schemes; the energy storage weight includes the battery pack weight M x 、Capacitor bank weight M y 、Battery converter weight M k1 、Capacitor converter weight M k2 sum;

[0023] Step S45, based on each m i The design scheme with the smallest energy storage weight in the corresponding design scheme group is obtained for all m i The design scheme corresponding to the smallest energy storage weight.

[0024] In some embodiments, the number of battery packs connected in series is N BS =U BZ / U B The number of parallel connected batteries N BP =MAX( NBP1 , N BP2 ), N BP1 =1000*P C / U BZ / Q B / C,N BP2 =1000*P C *T C / Q B / U BZ / 3600; the battery pack weight M x =N BS *N BP *M B ; The battery converter weight M k1 =MIN(M ka ); where N BP1 To satisfy P C Minimum number of battery packs in parallel; N BP2 To satisfy P C *T C Minimum number of battery packs connected in parallel.

[0025] In some embodiments, the number of capacitor groups connected in series is N CS =UCZ / U C ; The number of capacitor groups connected in parallel is N CP =2000*N CS *(P S -P C )*T S / Q C / (U CZ 2 -U CZmin 2 );The weight of the capacitor bank M y =N CS *N CP *M C ; The weight of the capacitor converter M k2 =MIN(M kb ); where U CZmin is the minimum voltage of the capacitor group.

[0026] In some embodiments, the electric energy demand in step S10 is the difference between the load power demand and the maximum output power of the engine; wherein the load power demand includes the power demand of electrical equipment and other equipment on the aircraft; and the load power demand is greater than the maximum output power of the engine.

[0027] In a second aspect, the present invention provides an aircraft energy storage device, the aircraft energy storage device is applied to an aircraft energy storage design method described in any one of the above embodiments, and the aircraft energy storage device includes:

[0028] A battery pack, a capacitor group, a battery converter, a capacitor converter, and a bus group; the battery pack includes multiple batteries of the same model; the capacitor group includes multiple capacitors of the same model; one end of the battery converter is electrically connected to the battery pack, and the other end is electrically connected to the bus group; one end of the capacitor converter is electrically connected to the capacitor group, and the other end is electrically connected to the bus group.

[0029] In order to solve the problem of how to quickly design a lightweight aircraft energy storage device, the present invention has the following advantages:

[0030] By obtaining the energy demand parameters, the available battery models, available capacitor models, available battery converter models, and available capacitor converter models are selected, and then the energy storage combination is listed, that is, the selection of batteries, capacitors, battery converters, and capacitor converters is determined. Then, based on the energy demand parameters, battery performance parameters, capacitor performance parameters, battery converter performance parameters, and capacitor converter performance parameters, the design scheme with the smallest energy storage weight is calculated and screened. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1A schematic diagram of an aircraft energy storage design method according to an embodiment is shown;

[0032] Figure 2 A schematic diagram of an aircraft energy storage device according to an embodiment is shown.

[0033] Reference numerals: 10 energy storage device; 11 battery group; 12 capacitor group; 13 battery converter; 14 capacitor converter; 15 busbar group. DETAILED DESCRIPTION

[0034] The present disclosure will now be discussed with reference to several exemplary embodiments. It should be understood that these embodiments are discussed only to enable those skilled in the art to better understand and thus implement the present disclosure, rather than implying any limitation on the scope of the present disclosure.

[0035] As used herein, the term "including" and its variants are to be interpreted as open-ended terms meaning "including but not limited to". The term "based on" is to be interpreted as "based at least in part on". The terms "one embodiment" and "an embodiment" are to be interpreted as "at least one embodiment". The term "another embodiment" is to be interpreted as "at least one other embodiment". The orientation or position relationship indicated by the terms "upper", "lower", "left", "right", "front", "back", "top", "bottom", "inner", "outer", "vertical", "horizontal", "lateral", "longitudinal" and the like is based on the orientation or position relationship shown in the accompanying drawings. These terms are mainly for better describing the present application and its embodiments, and are not used to limit the indicated devices, elements or components to have a specific orientation, or to be constructed and operated in a specific orientation. In addition, in addition to being used to indicate an orientation or position relationship, some of the above terms may also be used to indicate other meanings, such as the term "upper" may also be used to indicate a certain dependency or connection relationship in some cases. For those of ordinary skill in the art, the specific meanings of these terms in this application can be understood according to the specific circumstances. In addition, the terms "install", "set", "provided with", "connected" and "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral structure; it can be a mechanical connection, or an electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, or it can be an internal connection between two devices, elements or components. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood according to the specific circumstances. In addition, the terms "first", "second", etc. are mainly used to distinguish different devices, elements or components (the specific types and structures may be the same or different), and are not used to indicate or imply the relative importance and quantity of the indicated devices, elements or components. Unless otherwise specified, "plurality" means two or more.

[0036] In a first aspect, this embodiment discloses a method for designing energy storage for an aircraft, such as Figure 1 As shown, it may include:

[0037] Step S10, based on the aircraft's power demand for the aircraft energy storage device 10, obtaining energy demand parameters of the aircraft energy storage device 10;

[0038] Step S20, based on the acquired energy demand parameters, acquiring performance parameters of batteries of different models, performance parameters of capacitors of different models, performance parameters of battery converters 13 of different models, and performance parameters of battery converters 14 of different models;

[0039] Step S30, based on the performance parameters of batteries of different models, the performance parameters of capacitors of different models, the performance parameters of battery converters 13 of different models, the performance parameters of battery converters 14 of different models and the energy demand parameters, obtain the energy storage combination M={m i |1≤i},m i =(X k , Y j , A a , B b ); where m i Includes various battery pack models X k , various types of capacitor banks Y j , various types of battery converters 13A a , various types of battery converters 14B b ; 1≤k≤n1, 1≤j≤n2, 1≤a≤n3, 1≤b≤n4; n1, n2, n3, n4 are all natural numbers greater than 2; battery pack X k Including multiple batteries of the same model; capacitor bank Y j Including multiple capacitors of the same model;

[0040] Step S40, based on the energy storage combination M and the energy demand parameters, battery performance parameters, capacitor performance parameters, battery converter 13 performance parameters, and battery converter 14 performance parameters, obtain all m i The design scheme with the smallest energy storage weight corresponding to the design scheme includes the battery pack 11 connected in series with the number N BS 、N number of parallel connections of battery pack 11 BP 、Capacitor bank 12 series number N CS 、Capacitor bank 12 parallel number N CP ; Energy storage weight includes battery pack 11 weight M x 、Capacitor Bank 12 Weight M y 、Battery converter 13 weight M k1 、Battery converter 14 weight M k2 sum.

[0041] In this embodiment, if Figure 2 As shown, the aircraft energy storage device 10 may include a battery pack 11, a capacitor pack 12, a battery converter 13, a battery converter 14, and a busbar pack 15. One end of the battery converter 13 is electrically connected to the battery pack 11, and the other end is electrically connected to the busbar pack 15. One end of the battery converter 14 is electrically connected to the capacitor pack 12, and the other end is electrically connected to the busbar pack 15. Figure 1 As shown, the aircraft energy storage design method may include steps S10 to S40, and each step is described in detail as follows:

[0042] In step S10, based on the electric energy demand of the aircraft energy storage device 10 during the flight route, the energy demand parameters of the aircraft energy storage device 10, such as working power and working time, can be obtained to facilitate the subsequent design of the energy storage device 10 solution.

[0043] Step S20, based on the acquired energy demand parameters, the performance parameters of batteries of different models (such as battery voltage, battery weight, battery capacity, etc.), the performance parameters of capacitors of different models (such as capacitor voltage, capacitor weight, capacitor capacity, etc.), the performance parameters of battery converters 13 of different models (such as the upper and lower limits of the low-voltage side voltage of the battery converter 13, rated power, weight, etc.), and the performance parameters of battery converters 14 of different models (such as the upper and lower limits of the low-voltage side voltage of the battery converter 14, rated power, weight, etc.) can be acquired, so as to facilitate the subsequent acquisition of a suitable energy storage combination and the calculation of the number of batteries and capacitors in series and parallel.

[0044] Step S30, according to the performance parameters of different types of batteries, the performance parameters of different types of capacitors, the performance parameters of different types of battery converters 13, the performance parameters of different types of battery converters 14 and the energy demand parameters, the battery, capacitor, battery converter 13 and battery converter 14 are combined and selected to obtain the energy storage combination M={m i |1≤i},m i =(X k , Y j , A a , B b ), that is, m i Can include various types of battery packs X k , various types of capacitor banks Y j , various types of battery converters 13A a , various types of battery converters 14B b k is greater than or equal to 1 and less than or equal to n1, j is greater than or equal to 1 and less than or equal to n2, a is greater than or equal to 1 and less than or equal to n3, and b is greater than or equal to 1 and less than or equal to n4. n1, n2, n3, and n4 are all natural numbers greater than 2. Battery pack X k Can include multiple batteries of the same model, capacitor bank Yj Multiple capacitors of the same model may be included. The output voltages of the battery converter 13 and the battery converter 14 must meet the rated voltage of the busbar group 15. For example, when k=3, j=3, a=2, and b=2, there are 3 models of batteries, 3 models of capacitors, 2 models of battery converters 13, and 2 models of battery converters 14 to choose from, for a total of 3*3*2*2=36 permutations and combinations. i As an energy storage combination M.

[0045] Step S40, according to the energy storage combination M, energy demand parameters, battery performance parameters, capacitor performance parameters, battery converter 13 performance parameters, battery converter 14 performance parameters, each m can be calculated separately. i The number of battery packs 11 in series is N BS 、N number of parallel connections of battery pack 11 BP 、Capacitor bank 12 series number N CS 、Capacitor bank 12 parallel number N CP , then we can calculate each m i The corresponding energy storage weight (i.e., the weight of the battery pack 11 M x 、Capacitor Bank 12 Weight M y 、Battery converter 13 weight M k1 、Battery converter 14 weight M k2 The sum of all m can be obtained by comparing the energy storage weight. i The corresponding design scheme with the smallest energy storage weight can then quickly design an energy storage device 10 that meets the aircraft's power requirements and lightweight requirements.

[0046] In some embodiments, the energy demand parameter in step S10 includes an instantaneous maximum power demand P S , Instantaneous power duration T S , long-term maximum power demand P C , Long-term power duration T C ;P S Greater than P C ; T S Less than T C .

[0047] In this embodiment, the energy demand parameter in step S10 may include the instantaneous maximum power demand P S , Instantaneous power duration T S , long-term maximum power demand P C , Long-term power duration T C .P S Can be greater than P C . T S Can be less than T CFor example, P S It can be the maximum power requirement of the aircraft pulse weapon, and its single use duration can be T S , and P C Can be divided by P S The maximum power demand other than the power demand of the power source 10 can be determined, such as high-power radar, engine ground or flight operation, etc. This makes it easier to select and calculate the energy storage device 10.

[0048] In some embodiments, the aircraft energy storage design method further includes:

[0049] Step S11: based on the energy demand of the aircraft, obtain the first electrical equipment parameter W of the aircraft a =(P n , T n ); where P n is the power of the first electrical equipment, T n P n The corresponding working time of the first electrical equipment; 2≤n≤N, where N is the number of electrical equipment;

[0050] Step S12: based on the first electrical equipment parameter W a , obtain the instantaneous maximum power demand P S =MAX(P n ), instantaneous power duration T S P S The corresponding working hours of electrical equipment.

[0051] In this embodiment, the aircraft energy storage design method may further include step S11 and step S12. In step S11, according to the energy demand of the aircraft, the first electrical equipment parameter W of the aircraft may be obtained. a =(P n , T n ), which are the parameters of all devices on the aircraft that use electrical energy, among which P n is the power of the first electrical equipment, T n P n The corresponding working time of the first electric device. 2≤n≤N, N is the number of electric devices. In step S12, according to the acquired first electric device parameter W a , the instantaneous maximum power demand P can be obtained S =MAX(P n ), that is, P S It can be the maximum value of the power of all first electrical devices, and the instantaneous power duration T S P S The corresponding working time of the electrical equipment makes it easier to select and calculate the energy storage equipment.

[0052] In some embodiments, the aircraft energy storage design method further includes:

[0053] Step S13: Based on the first electrical equipment parameter W a and the instantaneous maximum power demand P S , obtain the second electrical equipment parameter W of the aircraft b =(P m , T m ); where W b W a Remove MAX (P n ) after the parameter, P m is the power of the second electrical equipment, T m P m The corresponding working time of the second electrical equipment; 1≤m≤N-1;

[0054] Step S14: based on the second electrical equipment parameter W b , obtain the long-term maximum power demand P C =MAX(P m ), long-term power duration T C =Q / P C ; Where Q is the maximum long-term energy demand; .

[0055] In this embodiment, the aircraft energy storage design method may further include steps S13 and S14. In step S13, according to the first electrical equipment parameter W obtained in step S11, a and the instantaneous maximum power demand P obtained in step S12 S , the second electrical equipment parameter W of the aircraft can be obtained b =(P m , T m ), where W b It can be W a Remove MAX (P n ) Parameters of the remaining electrical equipment, P m is the power of the second electrical equipment, T m P m The corresponding working time of the second electric device. 1≤m≤N-1. In step S14, according to the second electric device parameter W b , the long-term maximum power demand P can be obtained C =MAX(P m ), that is, P C It can be the maximum value among all the second electrical equipment powers. C =Q / P C , that is, long-term power duration T C is the long-term maximum energy demand Q and the long-term maximum power demand PC ratio. , that is, the second electrical equipment parameter W b The maximum of all energy requirements.

[0056] In some embodiments, the battery performance parameters in step S20 include the battery voltage U B 、Battery capacity Q B , battery discharge rate C, battery weight M B ; Capacitor performance parameters include capacitor voltage U C 、Capacitance Q C 、Capacitor weight M C ; Battery converter 13 performance parameters include low voltage side voltage limit U a1min , Low voltage side voltage upper limit U a1max , Rated power P wa 、Battery converter 13 weight M ka ;P C ≤P wa ; Battery converter 14 performance parameters include low voltage side voltage limit U a2min , Low voltage side voltage upper limit U a2max , Rated power P wb 、Battery converter 14 weight M kb ;P S -P C ≤P wb .

[0057] In this embodiment, the battery performance parameter in step S20 may include the battery voltage U B 、Battery capacity Q B , battery discharge rate C, battery weight M B Capacitor performance parameters may include capacitor voltage U C 、Capacitance Q C 、Capacitor weight M C The performance parameters of the battery converter 13 may include the low voltage side voltage lower limit U a1min , Low voltage side voltage upper limit U a1max , Rated power P wa 、Battery converter 13 weight M ka .P C ≤P wa The performance parameters of the battery converter 14 may include the low voltage side voltage lower limit U a2min , Low voltage side voltage upper limit U a2max , Rated power P wb 、Battery converter 14 weight M kb .P S -P C ≤P wbAccording to the above parameters, the models of battery converter 13 and battery converter 14 can be selected according to power requirements and minimum weight, and the number of battery packs 11 connected in series N can be calculated. BS 、N number of parallel connections of battery pack 11 BP 、Capacitor bank 12 series number N CS 、Capacitor bank 12 parallel number N CP , which facilitates the subsequent acquisition of energy storage weight to determine the design plan.

[0058] In some embodiments, step S40 includes:

[0059] Step S41, based on the energy storage combination M and the energy demand parameters, battery performance parameters, capacitor performance parameters, and converter performance parameters, i Battery Pack X k Set a U BZ The initial value of an m i The capacitor group Y in j Set a U CZ The initial value of BZ is the voltage of the battery pack 11; U a1min ≤U BZ ≤U a1max ; U CZ is the voltage of the capacitor bank 12; U a2min ≤U CZ ≤U a2max ;

[0060] Step S42, based on an m i Set a U BZ The initial value and U CZ The initial value of the battery pack 11 is connected in series with the number N. BS 、N number of parallel connections of battery pack 11 BP 、Capacitor bank 12 series number N CS 、Capacitor bank 12 parallel number N CP ;

[0061] Step S43, based on m i A corresponding design scheme is to adjust U according to the first interval threshold s1. BZ , adjust U according to the second interval threshold s2 CZ To obtain m i The remaining corresponding design solutions; 0<s1≤U a1max -U a1min ; 0<s2≤U a2max -U a2min ;

[0062] Step S44, based on m i The corresponding design solution group, obtain mi The design scheme with the smallest energy storage weight in the corresponding design scheme group; wherein the design scheme group includes multiple design schemes; the energy storage weight includes the weight M of the battery pack 11 x 、Capacitor Bank 12 Weight M y 、Battery converter 13 weight M k1 、Battery converter 14 weight M k2 sum;

[0063] Step S45, based on each m i The design with the smallest energy storage weight in the corresponding design group is obtained for all m i The design scheme with the smallest energy storage weight corresponds to .

[0064] In this embodiment, step S40 may include step S41 to step S45, and each step is described in detail as follows:

[0065] Step S41, according to the energy storage combination M, energy demand parameters, battery performance parameters, capacitor performance parameters, battery converter 13 performance parameters, battery converter 14 performance parameters, in an m i Battery Pack X k You can set a U BZ The initial value of an m i The capacitor group Y in j You can set a U CZ The initial value of U BZ is the voltage of the battery pack 11. a1min ≤U BZ ≤U a1max .U CZ is the voltage of the capacitor bank 12. a2min ≤U CZ ≤U a2max For example, U can be determined based on the performance parameters of the battery converter 13. a1min and U a1max The value of U can be determined according to the performance parameters of the battery converter 14. a2min and U a2max When U a1min =120V, U a1max =200V, the voltage U of the battery pack 11 BZ You can take any value in the range of 120V~200V as the initial value, such as U BZ =160V. When U a2min =100V,U a2max =200V, the voltage U of capacitor bank 12 CZ You can take any value in the range of 100V~200V as the initial value, such as U CZ =150V.

[0066] Step S42, according to an m i Set a U BZ The initial value and U CZ The initial value of can obtain a corresponding design scheme, that is, the number of battery packs 11 connected in series N can be calculated. BS 、N number of parallel connections of battery pack 11 BP 、Capacitor bank 12 series number N CS 、Capacitor bank 12 parallel number N CP .

[0067] Step S43, after obtaining an m i After a corresponding design is obtained, U can be adjusted according to the first interval threshold s1. BZ , adjust U according to the second interval threshold s2 CZ To obtain m i The remaining corresponding design solutions. 0<s1≤U a1max -U a1min , 0<s2≤U a2max -U a2min For example, at this time U BZ =160V,U CZ =150V is a random value within the allowable range and is not necessarily the best choice, so it is necessary to list U BZ and U CZ All possibilities, according to the first interval threshold s1 = 1V, the second interval threshold s2 = 1V, then U BZ The possible values ​​are 120V, 121V, 122V, ... 200V, a total of 80 possible values, U CZ The possible values ​​are 100V, 101V, 102V...200V, a total of 100 possibilities, so there are a total of 80*100=8000 possibilities, that is, 8000 design solutions, and U BZ =160V,U CZ =150V is just one of them.

[0068] Step S44, according to m i A plurality of design schemes are formed into a corresponding design scheme group, and the design scheme with the smallest energy storage weight can be selected. The energy storage weight can be the weight M of the battery pack 11. x 、Capacitor Bank 12 Weight M y 、Battery converter 13 weight M k1 、Battery converter 14 weight M k2 sum.

[0069] Step S45, according to each m i The design with the smallest energy storage weight in the corresponding design group can bei The design scheme with the minimum energy storage is selected, so that the optimal design scheme of the energy storage device 10 can be determined to meet the electrical energy demand and lightweight demand of the aircraft.

[0070] In some embodiments, the number of battery packs 11 connected in series is N BS =U BZ / U B ; Battery pack 11 parallel number N BP =MAX(N BP1 , N BP2 ), N BP1 =1000*P C / U BZ / Q B / C,N BP2 =1000*P C *T C / Q B / U BZ / 3600; Battery pack 11 weight M x =N BS *N BP *M B ; Battery converter 13 weight M k1 =MIN(M ka ); where N BP1 To satisfy P C Minimum number of batteries in parallel: N BP2 To satisfy P C *T C The minimum number of batteries connected in parallel is 11.

[0071] In this embodiment, the number of battery packs 11 connected in series is N. BS Mainly subject to voltage constraints, which can be the voltage U of the battery pack 11 BZ and battery voltage U B The number of parallel connections of battery packs 11 is N BP Subject to both power and energy constraints, it can be C The minimum number of parallel connections of 11 batteries is N BP1 and satisfy P C *T C The minimum number of parallel connections of 11 batteries is N BP2 The maximum value of the battery converter 13 is M. k1 It can be P wa Greater than or equal to P C The corresponding M of the multiple battery converters 13 ka The minimum value. Battery pack 11 weight M x It can be the number of batteries 11 connected in series N BS 、N number of parallel connections of battery pack 11 BP 、M BThe product result between .

[0072] For example, in the energy demand parameters, the instantaneous maximum power demand P S =100kW, instantaneous power duration T S =3s; long-term maximum power demand P C =20kW, long-term power duration T C =300s. Among the battery performance parameters, the battery voltage U B =3.6V, battery capacity Q B =4Ah, battery discharge rate C=8, battery weight M B =0.07kg. Among the parameters of battery converter 13, the lower limit of low voltage side voltage U a1min =120V, low voltage side voltage upper limit U a1max =200V, rated power P wa =20kw. a1min =120V, U a1max =200V, the voltage U of the battery pack 11 BZ You can take any value in the range of 120V~200V as the initial value, such as U BZ =144V. According to the above parameter values, the number of battery packs 11 connected in series is N BS =U BZ / U B =144 / 3.6=40. N BP1 =P C / U BZ / Q B / C=20000 / 144 / 4 / 8=4.3, take 5; N BP2 =P C *T C / Q B / U BZ / 3600=20000*300 / 4 / 144 / 3600=2.89, take 3; the number of parallel connections of battery pack 11 is N BP =MAX(N BP1 , N BP2 ) = 5. Battery pack 11 weight M x =N BS *N BP *M B =40*5*0.07=14kg. wa =20kw, the battery converter 13 can have a corresponding battery converter 13 weight M according to the product model. k1 =7kg.

[0073] In some embodiments, the number of capacitors in series 12 is N CS =U CZ / UC ; Capacitor bank 12 parallel connections N CP =2000*N CS *(P S -P C )*T S / Q C / (U CZ 2 -U CZmin 2 ); Capacitor bank 12 weight M y =N CS *N CP *M C ; Battery converter 14 weight M k2 =MIN(M kb ); where U CZmin is the minimum voltage of the capacitor group 12.

[0074] In this embodiment, the number of capacitor groups 12 connected in series is N. CS Mainly subject to voltage constraints, which can be the voltage U of the capacitor bank 12 CZ and capacitor voltage U C The ratio of capacitor group 12 is connected in parallel. CP Mainly subject to energy constraints, it can be calculated according to the formula N CP =2000*N CS *(P S -P C )*T S / Q C / (U CZ 2 -U CZmin 2 ) is obtained, where U CZmin is the minimum voltage of the capacitor bank 12. The weight of the capacitor bank 12 is M y It can be a capacitor bank with 12 series connections, number N CS 、Capacitor bank 12 parallel number N CP 、Capacitor weight M C The product of the two is: k2 It can be P wb Greater than or equal to (P S -P C ) of the plurality of battery converters 14 corresponding to M kb The smallest value.

[0075] For example, in the energy demand parameters, the instantaneous maximum power demand P S =100kW, instantaneous power duration T S =3s; long-term maximum power demand P C =20kW, long-term power duration T C=300s. Among the capacitor performance parameters, capacitor voltage U C =3V, capacitor capacity Q C =2000F, capacitor weight M C =0.08kg. Among the performance parameters of the battery converter 14, the lower limit of the low voltage side voltage U a2min =100V, low voltage side voltage upper limit U a2max =200V, rated power P wb =80kw. a2min =100V,U a2max =200V, the voltage U of capacitor bank 12 CZ You can take any value in the range of 100V~200V as the initial value, such as U CZ =144V. Number of capacitors in series N CS =U CZ / U C =144 / 3=48. Number of capacitors in parallel N CP =2000*N CS *(P S -P C )*T S / Q C / (U CZ 2 -U CZmin 2 )=2000*48*(100-20)*3 / 2000 / (144*144-100*100)=1.1, take 2. Capacitor bank 12 weight M y =N CS *N CP *M C =48*2*0.08=7.68kg. wb =80kw, the battery converter 14 can have a corresponding battery converter 13 weight M according to the product model k2 =20kg. In summary, the energy storage weight is M x +M y +M k1 +M k2 =14+7.68+7+20=48.68kg. i After calculating the corresponding energy storage weight, the design scheme with the smallest energy storage weight can be selected, thereby determining the optimal design scheme of the energy storage device 10 to meet the electrical energy demand and lightweight requirements of the aircraft.

[0076] In some embodiments, the power demand in step S10 is the difference between the load power demand and the maximum output power of the engine; wherein the load power demand includes the power demand of electrical equipment and other equipment on the aircraft; and the load power demand is greater than the maximum output power of the engine.

[0077] In this embodiment, when the load power demand (i.e., the power demand of electrical equipment and other equipment on the aircraft) is greater than the maximum output power of the engine, the power demand in step S10 can be the difference between the load power demand and the maximum output power of the engine, which facilitates the subsequent acquisition of the energy demand parameters of the energy storage device 10.

[0078] In a second aspect, this embodiment discloses an aircraft energy storage device 10, such as Figure 2 As shown, it may include:

[0079] A battery group 11, a capacitor group 12, a battery converter 13, a battery converter 14, and a bus group 15; the battery group 11 includes multiple batteries of the same model; the capacitor group 12 includes multiple capacitors of the same model; one end of the battery converter 13 is electrically connected to the battery group 11, and the other end is electrically connected to the bus group 15; one end of the battery converter 14 is electrically connected to the capacitor group 12, and the other end is electrically connected to the bus group 15.

[0080] In this embodiment, the energy storage device 10 may include a battery pack 11, a capacitor pack 12, a battery converter 13, a battery converter 14, and a bus group 15. The battery pack 11 may include multiple batteries of the same model. The capacitor pack 12 may include multiple capacitors of the same model. One end of the battery converter 13 is electrically connected to the battery pack 11, and the other end is electrically connected to the bus group 15. One end of the battery converter 14 is electrically connected to the capacitor pack 12, and the other end is electrically connected to the bus group 15. Thus, electrical energy can be transmitted through the bus group 15 to meet the electrical energy demand of the aircraft.

[0081] Those skilled in the art will appreciate that the above-mentioned embodiments are specific examples for implementing the present disclosure, and in actual applications, various changes may be made thereto in form and detail without departing from the spirit and scope of the present disclosure.

Claims

1. A method for designing aircraft energy storage, characterized in that: The aircraft energy storage design method comprises: Step S10, based on the electric energy demand of the aircraft for the aircraft energy storage device, obtaining energy demand parameters of the aircraft energy storage device; Step S20, based on the energy demand parameter obtained, obtaining battery performance parameters of different models, capacitor performance parameters of different models, battery converter performance parameters of different models, and capacitor converter performance parameters of different models; Step S30, based on the battery performance parameters of different models, the capacitor performance parameters of different models, the battery converter performance parameters of different models, the capacitor converter performance parameters of different models and the energy demand parameters, obtain the energy storage combination M={m i |1≤i},mi=(X k , Y j , A a , B b ); wherein, the m i Includes various battery pack models X k , various types of capacitor banks Y j 、Various types of battery converters A a , various types of capacitor converters B b ; 1≤k≤n1, 1≤j≤n2, 1≤a≤n3, 1≤b≤n4; n1, n2, n3, n4 are all natural numbers greater than 2; the battery pack X k comprising a plurality of batteries of the same type; the capacitor group Y j Including multiple capacitors of the same model; Step S40, based on the energy storage combination M and the energy demand parameter, the battery performance parameter, the capacitor performance parameter, the battery converter performance parameter, and the capacitor converter performance parameter, obtain all m i The design scheme with the smallest energy storage weight corresponding to the design scheme; wherein the design scheme includes the number of battery packs connected in series N BS 、N number of battery packs in parallel BP 、Number of capacitors in series CS 、Number of capacitors in parallel CP The energy storage weight includes the battery pack weight M x 、Capacitor bank weight M y 、Battery converter weight M k1 , capacitor converter weight M k2 sum.

2. The method for designing aircraft energy storage according to claim 1, characterized in that: The energy demand parameters in step S10 include the instantaneous maximum power demand P S , Instantaneous power duration T S , long-term maximum power demand P C , Long-term power duration T C ;P S Greater than P C ; T S Less than T C .

3. The method for designing aircraft energy storage according to claim 2, characterized in that: The aircraft energy storage design method also includes: Step S11: based on the energy demand of the aircraft, obtain the first electrical equipment parameter W of the aircraft a =(P n , T n ); where P n is the power of the first electrical equipment, T n P n The corresponding working time of the first electrical equipment; 2≤n≤N, where N is the number of electrical equipment; Step S12: based on the first electrical equipment parameter W a , obtain the instantaneous maximum power demand P S =MAX(P n ), the instantaneous power duration T S P S The corresponding working hours of electrical equipment.

4. The method for designing aircraft energy storage according to claim 3, characterized in that: The aircraft energy storage design method also includes: Step S13: based on the first electrical equipment parameter W a and the instantaneous maximum power demand P S , obtain the second electrical equipment parameter W of the aircraft b =(P m , T m ); where W b W a Remove MAX (P n ) after the parameter, P m is the power of the second electrical equipment, T m P m The corresponding working time of the second electrical equipment; 1≤m≤N-1; Step S14: based on the second electrical equipment parameter W b , obtain the long-term maximum power demand P C =MAX(P m ), the long-term power duration T C =Q / P C ; Where Q is the maximum long-term energy demand; .

5. The method for designing aircraft energy storage according to claim 1, characterized in that: The battery performance parameters in step S20 include the battery voltage U B 、Battery capacity Q B , battery discharge rate C, battery weight M B ; The capacitor performance parameters include capacitor voltage U C 、Capacitance Q C 、Capacitor weight M C The battery converter performance parameters include the low voltage side voltage lower limit U a1min , Low voltage side voltage upper limit U a1max , Rated power P wa 、The battery converter weight M ka ;P C ≤P wa The performance parameters of the capacitor converter include the lower limit of the low voltage side voltage U a2min , Low voltage side voltage upper limit U a2max , Rated power P wb , the weight of the capacitor converter M kb ;P S -P C ≤P wb .

6. The method for designing aircraft energy storage according to claim 5, characterized in that: The step S40 comprises: Step S41, based on the energy storage combination M and the energy demand parameter, the battery performance parameter, the capacitor performance parameter, and the converter performance parameter, i The battery pack X k Set a U BZ The initial value of an m i The capacitor group Y j Set a U CZ The initial value of BZ is the voltage of the battery pack; U a1min ≤U BZ ≤U a1max ; U CZ is the voltage of the capacitor bank; U a2min ≤U CZ ≤U a2max ; Step S42, based on an m i Set a U BZ The initial value and U CZ The initial value of the battery pack is obtained by obtaining a corresponding design scheme; wherein the design scheme includes the number of battery packs in series N BS , the number of parallel connected battery packs N BP The number of capacitors connected in series is N CS , the number of capacitor groups connected in parallel N CP ; Step S43, based on the m i A corresponding design scheme is to adjust U according to the first interval threshold s1. BZ , adjust U according to the second interval threshold s2 CZ To obtain the m i The remaining corresponding design schemes; 0<s1≤U a1max -U a1min ; 0<s2≤U a2max -U a2min ; Step S44, based on the m i The corresponding design solution group obtains the m i The design scheme with the smallest energy storage weight in the corresponding design scheme group; wherein the design scheme group includes multiple design schemes; the energy storage weight includes the battery pack weight M x 、Capacitor bank weight M y 、Battery converter weight M k1 , capacitor converter weight M k2 sum; Step S45, based on each m i The design scheme with the smallest energy storage weight in the corresponding design scheme group is obtained for all m i The design scheme with the smallest energy storage weight corresponds to the one in the figure.

7. The method for designing aircraft energy storage according to claim 6, characterized in that: The number of battery packs connected in series is N BS =U BZ / U B The number of parallel connected batteries N BP =MAX(N BP1 , N BP2 ), N BP1 =1000*P C / U BZ / Q B / C,N BP2 =1000*P C *T C / Q B / U BZ / 3600; the battery pack weight Mx=N BS *N BP *M B ; The battery converter weight M k1 =MIN(M ka ); Among them, N BP1 To satisfy P C Minimum number of battery packs in parallel; N BP2 To satisfy P C *T C Minimum number of battery packs connected in parallel.

8. The method for designing aircraft energy storage according to claim 7, characterized in that: The number of capacitors in series is N CS =U CZ / U C ; The number of capacitor groups connected in parallel is N CP =2000*N CS *(P S -P C )*T S / Q C / (U CZ 2 -U CZmin 2 );The weight of the capacitor bank M y =N CS *N CP *M C ; The weight of the capacitor converter M k2 =MIN(M kb ); Among them, U CZmin is the minimum voltage of the capacitor group.

9. The method for designing aircraft energy storage according to claim 1, characterized in that: The electric energy demand in step S10 is the difference between the load power demand and the maximum output power of the engine; wherein the load power demand includes the power demand of electrical equipment and other equipment on the aircraft; and the load power demand is greater than the maximum output power of the engine.

10. An aircraft energy storage device, the aircraft energy storage device is applied to an aircraft energy storage design method according to any one of claims 1 to 9, characterized in that: The aircraft energy storage device comprises: A battery pack, a capacitor group, a battery converter, a capacitor converter, and a bus group; the battery pack includes multiple batteries of the same model; the capacitor group includes multiple capacitors of the same model; one end of the battery converter is electrically connected to the battery pack, and the other end is electrically connected to the bus group; one end of the capacitor converter is electrically connected to the capacitor group, and the other end is electrically connected to the bus group.

Images