阅读说明：本技术 单通道多电飞机发电机控制器gcu的持续未钦定功率源保护结构 (continuous unfixed power source protection structure of single-channel multi-electric-aircraft generator controller GCU ) 是由 万波 于 2018-05-31 设计创作，主要内容包括：本发明公开单通道多电飞机发电机控制器GCU的持续未钦定功率源保护结构,包含有,发电机控制器GCU用于感测发电机断路器处的电压电流,若发电机的无功功率输出低于阈值,则发电机控制器GCU执行持续未钦定功率源保护动作。本发明的有益效果在于,防止非预期的多台发电机并联。(The invention discloses a continuous unfixed power source protection structure of a generator controller GCU of a single-channel multi-electric-aircraft, which comprises the generator controller GCU, wherein the generator controller GCU is used for sensing voltage and current at a breaker of a generator, and if the reactive power output of the generator is lower than a threshold value, the generator controller GCU executes a continuous unfixed power source protection action. The invention has the beneficial effect of preventing unexpected multiple generators from being connected in parallel.)

1. a continuous unfixed power source protection structure of a single-channel multi-electric-aircraft generator controller GCU is characterized by comprising,

The main generator GEN L is connected with the first end of the circuit breaker L GCB, and the second end of the circuit breaker L GCB is connected with the Bus bar L235 VAC Bus;

the GEN R of the main generator is connected with the first end of the circuit breaker R GCB, and the second end of the circuit breaker R GCB is connected with the Bus bar R235 VAC Bus;

The auxiliary generator APU GEN is connected with the first end of the circuit breaker APB, the Bus bar L235 VAC Bus is connected with the first end of the contactor L BTB, the Bus bar R235 VAC Bus is connected with the first end of the contactor R BTB, and the second end of the contactor APB is connected with the second end of the contactor L BTB and the second end of the contactor R BTB respectively;

the main generator GEN L is provided with a generator controller L GCU, the generator controller L GCU is used for sensing voltage and current at the circuit breaker L GCB, and if the reactive power output of the main generator GEN L is lower than a first threshold value, the generator controller L GCU executes continuous unfired power source protection action;

The main generator GEN R has a generator controller rccu for sensing the voltage current at the circuit breaker rcgb, the generator controller rccu performing a continuous unfired power source protection action if the reactive power output of the main generator GEN R is below a second threshold;

The auxiliary generator APU GEN has a generator controller AGCU for sensing the voltage current at the circuit breaker APB, and if the reactive power output of the auxiliary generator APU GEN is below a third threshold, the generator controller AGCU performs a continuous unclassified power source protection action.

2. The continuous unclamping power source protection architecture for the single-channel multi-electric aircraft generator controller GCU of claim 1, wherein the first threshold, the second threshold, and the third threshold are all 0.85.

3. The continuous unclassified power source protection architecture of a single-channel multi-electric aircraft generator controller GCU according to claim 1 or 2,

the Bus bar L235 VAC Bus is connected with a first end of a contactor L ATUC, a second end of the contactor L ATUC is connected with an electric energy conversion device L ATU, the electric energy conversion device L ATU is connected with a first end of a contactor L BSB, and a second end of the contactor L BSB is connected with the Bus bar L115 VAC Bus;

The Bus bar R235 VAC Bus is connected with a first end of a contactor R ATUC, a second end of the contactor R ATUC is connected with an electric energy conversion device R ATU, the electric energy conversion device R ATU is connected with a first end of a contactor R BSB, and a second end of the contactor R BSB is connected with the Bus bar R115 VAC Bus;

a ground power supply L FWD EP is connected with a first end of a contactor L EPC, and a second end of the contactor L EPC is connected with a first end of a contactor L BSB;

a ground power supply R FWD EP is connected with a first end of a contactor R EPC, and a second end of the contactor R EPC is connected with a first end of a contactor R BSB;

The Bus bar L235 VAC Bus is connected with the first end of the contactor LacT, the second end of the contactor LacT is connected with the first end of the contactor RacT, and the second end of the contactor RacT is connected with the Bus bar R235 VAC Bus;

The second end of the contactor L ATUC is connected with the first end of the contactor L TRU Rly, the second end of the contactor L TRU Rly is connected with the power conversion device TRU L, and the power conversion device TRU L is connected with the Bus bar L28 VDC Bus;

The second end of the contactor R ATUC is connected with the first end of the contactor R TRU Rly, the second end of the contactor R TRU Rly is connected with the power conversion device TRU R, and the power conversion device TRU R is connected with the Bus bar R28 VDC Bus;

The Bus bar L28 VDC Bus is connected with a first end of a contactor LdcT, a second end of the contactor LdcT is connected with a first end of a contactor RdcT, and a second end of the contactor RdcT is connected with the Bus bar R28 VDC Bus;

the second end of the contactor L ATUC is connected with the first end of the contactor E1 TRU ISO Rly, the second end of the contactor E1 TRU ISO Rly is respectively connected with the first ends of a power conversion device TRU 1 and a contactor E1 TRU Rly, the power conversion device TRU 1 is further connected with the first end of a Bus bar ESS 128 VDC Bus, the second end of the contactor ESS ISO Rly is connected with a Bus bar ESS 235VAC Bus, the Bus bar ESS 235VAC Bus is connected with a power conversion device TRU 2, and the power conversion device TRU E2 is further connected with the Bus bar ESS 228 VDC Bus;

The generator GEN RAT is connected with a first end of a contactor RCB, and a second end of the contactor RCB is connected with a Bus bar ESS 235VAC Bus;

Bus ESS 128 VDC Bus is connected to the first terminal of contact E1T, the second terminal of contact E1T is connected to the first terminal of contact E2T, and the second terminal of contact E2T is connected to Bus ESS 228 VDC Bus;

bus ESS 128 VDC Bus is connected to a first terminal of contactor MBR, and a second terminal of contactor MBR is connected to Bus Hot BB 1;

the bus bar Hot BB2 is connected with a first end of a contactor SPUC, a second end of the contactor SPUC is connected with an SPU, the SPU is connected with a first end of a contactor SPUB, and a second end of the contactor SPUB is connected with an ATRU R;

the Bus bar L235 VAC Bus is connected with a first end of a contactor L ATRUC, a second end of the contactor L ATRUC is connected with an autotransformer rectifier ATRU L, and the autotransformer rectifier ATRU L is connected with the Bus bar L270 VDC Bus;

the Bus bar R235 VAC Bus is connected with the first end of the contactor R ATRUC, the second end of the contactor R ATRUC is connected with the autotransformer rectifier ATRU R, and the autotransformer rectifier ATRU R is connected with the Bus bar R270 VDC Bus;

An external power source L AFT EP is connected with a first end of a contactor L AEPC, and a second end of the contactor L AEPC is connected with an autotransformer rectifier ATRU L.

4. The continuous unclassified power source protection structure of the generator controller GCU of the single-channel multi-electric-aircraft according to claim 3, wherein the power supply of the main generator GEN L and the power supply of the main generator GEN R are variable frequency generators with rated power of 225kVA and rated voltage of 235 VAC; the auxiliary generator APU GEN is a variable frequency generator with rated power of 200kVA and rated voltage of 235 VAC; the generator GEN RAT is a variable frequency generator with rated power of 50kVA and rated voltage of 235 VAC; rated voltages of the ground power supply LFWD EP, the ground power supply R FWD EP and the third external power supply L AFT EP are 115 VAC; rated power of the ATRU L and the ATRU R is 150kVA, rated capacity of the ATU and the ATU is 60kVA, and rated output current of the TRU L, the TRU R, the TRU E1 and the TRU E2 is 240A; both the battery Main BAT and the battery APUBAT are batteries having a rated voltage of 28VDC and a capacity of 75 Ah.

Technical Field

The invention relates to a continuous unfixed power source protection structure of a single-channel multi-electric aircraft generator controller GCU.

Background

the Generator Controller Unit (GCU) has two functions, one is to provide excitation regulation for the Generator and the other is to provide protection for the Generator and the main power bus.

the conventional aircraft adopts a 115VAC/400Hz power supply system, the output frequency of the aircraft is constant, and a plurality of generators can be operated in parallel to improve the output power of a single generator, for example, in a B474 power supply system, a mode of operating 4 generators in parallel is adopted, as shown in FIG. 1. The multi-electric aircraft adopts a Variable Frequency Start Generator (VFSG), and because the output frequencies of the generators are different, the generators are independently operated under normal conditions and are not connected in parallel.

Under the multi-electric airplane architecture, unexpected parallel connection of a plurality of generators is prevented so as to prevent the generators from being damaged. For example, accidental closing of the connecting bus bar contactor may cause multiple generators to operate in Parallel, which is also referred to as a Sustained Parallel power Source (SPS) condition.

Disclosure of Invention

the invention aims to solve the technical problem of preventing unexpected parallel connection of a plurality of generators and provides a continuous unfixed power source protection structure of a single-channel multi-electric-aircraft generator controller GCU.

In order to achieve the purpose, the technical scheme of the invention is as follows: a continuous unfixed power source protection structure of a single-channel multi-electric-aircraft generator controller GCU comprises,

the main generator GEN L is connected with the first end of the circuit breaker L GCB, and the second end of the circuit breaker L GCB is connected with the Bus bar L235 VAC Bus;

The GEN R of the main generator is connected with the first end of the circuit breaker R GCB, and the second end of the circuit breaker R GCB is connected with the Bus bar R235 VAC Bus;

the auxiliary generator APU GEN is connected with the first end of the circuit breaker APB, the Bus bar L235 VAC Bus is connected with the first end of the contactor L BTB, the Bus bar R235 VAC Bus is connected with the first end of the contactor R BTB, and the second end of the contactor APB is connected with the second end of the contactor L BTB and the second end of the contactor R BTB respectively;

The main generator GEN L is provided with a generator controller L GCU, the generator controller L GCU is used for sensing voltage and current at the circuit breaker L GCB, and if the reactive power output of the main generator GEN L is lower than a first threshold value, the generator controller L GCU executes continuous unfired power source protection action;

The main generator GEN R has a generator controller rccu for sensing the voltage current at the circuit breaker rcgb, the generator controller rccu performing a continuous unfired power source protection action if the reactive power output of the main generator GEN R is below a second threshold;

the auxiliary generator APU GEN has a generator controller AGCU for sensing the voltage current at the circuit breaker APB, and if the reactive power output of the auxiliary generator APU GEN is below a third threshold, the generator controller AGCU performs a continuous unclassified power source protection action.

As a preferred scheme of the continuous unfixed power source protection structure of the single-channel multi-electric aircraft generator controller GCU, the first threshold, the second threshold and the third threshold are all 0.85.

As a preferred scheme of a continuous unfixed power source protection structure of a single-channel multi-electric-aircraft generator controller GCU, a Bus bar L235 VAC Bus is connected with a first end of a contactor L ATUC, a second end of the contactor L ATUC is connected with an electric energy conversion device L ATU, the electric energy conversion device L ATU is connected with a first end of a contactor L BSB, and a second end of the contactor L BSB is connected with a Bus bar L115 VAC Bus;

The Bus bar R235 VAC Bus is connected with a first end of a contactor R ATUC, a second end of the contactor R ATUC is connected with an electric energy conversion device R ATU, the electric energy conversion device R ATU is connected with a first end of a contactor R BSB, and a second end of the contactor R BSB is connected with the Bus bar R115 VAC Bus;

a ground power supply L FWD EP is connected with a first end of a contactor L EPC, and a second end of the contactor L EPC is connected with a first end of a contactor L BSB;

a ground power supply R FWD EP is connected with a first end of a contactor R EPC, and a second end of the contactor R EPC is connected with a first end of a contactor R BSB;

The Bus bar L235 VAC Bus is connected with the first end of the contactor LacT, the second end of the contactor LacT is connected with the first end of the contactor RacT, and the second end of the contactor RacT is connected with the Bus bar R235 VAC Bus;

The second end of the contactor L ATUC is connected with the first end of the contactor L TRU Rly, the second end of the contactor L TRU Rly is connected with the power conversion device TRU L, and the power conversion device TRU L is connected with the Bus bar L28 VDC Bus;

The second end of the contactor R ATUC is connected with the first end of the contactor R TRU Rly, the second end of the contactor R TRU Rly is connected with the power conversion device TRU R, and the power conversion device TRU R is connected with the Bus bar R28 VDC Bus;

The Bus bar L28 VDC Bus is connected with a first end of a contactor LdcT, a second end of the contactor LdcT is connected with a first end of a contactor RdcT, and a second end of the contactor RdcT is connected with the Bus bar R28 VDC Bus;

The second end of the contactor L ATUC is connected with the first end of the contactor E1 TRU ISO Rly, the second end of the contactor E1 TRU ISO Rly is respectively connected with the first ends of a power conversion device TRU 1 and a contactor E1 TRU Rly, the power conversion device TRU 1 is further connected with the first end of a Bus bar ESS 128 VDC Bus, the second end of the contactor ESS ISO Rly is connected with a Bus bar ESS 235VAC Bus, the Bus bar ESS 235VAC Bus is connected with a power conversion device TRU 2, and the power conversion device TRU E2 is further connected with the Bus bar ESS 228 VDC Bus;

The generator GEN RAT is connected with a first end of a contactor RCB, and a second end of the contactor RCB is connected with a Bus bar ESS 235VAC Bus;

Bus ESS 128 VDC Bus is connected to the first terminal of contact E1T, the second terminal of contact E1T is connected to the first terminal of contact E2T, and the second terminal of contact E2T is connected to Bus ESS 228 VDC Bus;

Bus ESS 128 VDC Bus is connected to a first terminal of contactor MBR, and a second terminal of contactor MBR is connected to Bus Hot BB 1;

The bus bar Hot BB2 is connected with a first end of a contactor SPUC, a second end of the contactor SPUC is connected with an SPU, the SPU is connected with a first end of a contactor SPUB, and a second end of the contactor SPUB is connected with an ATRU R;

the Bus bar L235 VAC Bus is connected with a first end of a contactor L ATRUC, a second end of the contactor L ATRUC is connected with an autotransformer rectifier ATRU L, and the autotransformer rectifier ATRU L is connected with the Bus bar L270 VDC Bus;

the Bus bar R235 VAC Bus is connected with the first end of the contactor R ATRUC, the second end of the contactor R ATRUC is connected with the autotransformer rectifier ATRU R, and the autotransformer rectifier ATRU R is connected with the Bus bar R270 VDC Bus;

an external power source L AFT EP is connected with a first end of a contactor L AEPC, and a second end of the contactor L AEPC is connected with an autotransformer rectifier ATRU L.

as an optimal scheme of a continuous unfixed power source protection structure of a generator controller GCU of a single-channel multi-electric-aircraft, a main generator GEN L supplies power and a main generator GEN R are variable-frequency generators with rated power of 225kVA and rated voltage of 235 VAC; the auxiliary generator APU GEN is a variable frequency generator with rated power of 200kVA and rated voltage of 235 VAC; the generator GEN RAT is a variable frequency generator with rated power of 50kVA and rated voltage of 235 VAC; rated voltages of the ground power supply L FWD EP, the ground power supply R FWD EP and the third external power supply L AFT EP are 115 VAC; rated power of the ATRU L and the ATRU R is 150kVA, rated capacity of the ATU and the ATU is 60kVA, and rated output current of the TRU L, the TRU R, the TRU E1 and the TRU E2 is 240A; the storage battery Main BAT and the storage battery APU BAT are both storage batteries with rated voltage of 28VDC and capacity of 75 Ah.

Compared with the prior art, the invention has the beneficial effects that:

1. Preventing unintended multiple generators from being connected in parallel.

2. Introducing a 235VAC bus bar to replace the 115VAC bus bar of a conventional aircraft, the power rating increases.

3. A 270VDC voltage level was introduced for speed regulation of large motors (air conditioning compressors, etc.).

4. the number of external power supply sockets is changed from 1 socket of a traditional airplane to 2, and meanwhile, the voltage class and the capacity of the emergency power supply RAT are increased from the original 115VAC 30kVA to 235VAC 50 kVA.

in addition to the technical problems addressed by the present invention, the technical features constituting the technical solutions, and the advantageous effects brought by the technical features of the technical solutions described above, other technical problems solved by the present invention, other technical features included in the technical solutions, and advantageous effects brought by the technical features will be described in further detail with reference to the accompanying drawings.

Drawings

Fig. 1 is a schematic view of a prior art structure.

Fig. 2 is a schematic structural diagram of an embodiment of the present invention.

Fig. 3 is a schematic diagram of a persistent unclamping power source protection information acquisition point according to an embodiment of the invention.

FIG. 4 is a control logic diagram of the power generation controller in an embodiment of the present invention.

Detailed Description

The present invention will be described in further detail below with reference to specific embodiments and drawings. Here, the description of the embodiments is provided to help understanding of the present invention, but the present invention is not limited thereto. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.

The embodiment relates to a novel continuous unfixed power source protection structure of a single-channel multi-electric aircraft generator controller GCU. The system comprises a left variable-frequency main starting generator GEN L and a right variable-frequency main starting generator GEN R with the rated power of 225kVA, an APU starting generator with the rated power of 200kVA, and an RAT generator with the rated power of 50 kVA. There are also three external power sources, L FWD EP, R FWD EP and L AFT EP, respectively, the outlets of each of which can support a maximum of 90kVA of power. The rated voltages of the main starter generator, the APU starter generator and the RAT generator are all 235VAC, and the rated voltages of the three external power supplies are 115 VAC. GEN L, GEN R and APU GEN are provided with respective generator breakers LGCB, R GCB and APB to control the switching of the generators, and in addition, the 3 generators are also provided with corresponding contactors L GNR, R GNR and A GNR to control the connection with a ground network. The three external power supplies also have corresponding contactors for controlling the access of the power supplies, namely L EPC, R EPC and L AEPC.

the secondary power supply of the power supply system comprises 2 ATRUs with rated power of 150kVA, two ATUs with rated capacity of 60kVA and 4 TRUs with rated output current of 240A. Wherein, the ATRU converts 235VAC into +/-270VDC, and respectively outputs the +/-270VDC to the left and right buses for supplying power to multi-electrical loads (flight control actuation, electrical ring control and the like); the ATU converts 230VAC into 115VAC, and respectively outputs the 115VAC to the left and right 115VAC bus bars; the TRU converts 235VAC into 28VDC, and outputs the 28VDC normal bus bars and the 28VDC emergency bus bars to the left and right.

the power supply system has two batteries with the rated voltage of 28VDC and the capacity of 75Ah, namely a main battery and an APU battery, and the batteries can supply power to key electronic equipment before the aircraft generator is started. Meanwhile, the APU battery can also be used to start the APU.

Referring to fig. 2, the main generator GEN L is connected to a first terminal of the circuit breaker L GCB, and a second terminal of the circuit breaker L GCB is connected to the Bus bar L235 VAC Bus.

the main generator GEN R is connected with the first end of the circuit breaker R GCB, and the second end of the circuit breaker R GCB is connected with the Bus bar R235 VAC Bus.

Auxiliary generator APU GEN links to each other with circuit breaker APB's first end, and busbar L235 VAC Bus links to each other with contactor L BTB's first end, and busbar R235 VAC Bus links to each other with contactor R BTB's first end, and contactor APB's second end links to each other with contactor L BTB's second end and contactor R BTB's second end respectively.

the main generator GEN L has a generator controller L GCU for sensing the voltage current at the circuit breaker L GCB (as shown in fig. 3).

the main generator GEN R has a generator controller rgcu for sensing the voltage current at the circuit breaker rgcb (as shown in fig. 3).

the auxiliary generator APU GEN has a generator controller a GCU for sensing the voltage current at the circuit breaker APB (as shown in fig. 3).

Busbar L235 VAC Bus links to each other with contactor L ATUC's first end, and contactor L ATUC's second end links to each other with electric energy conversion device L ATU, and electric energy conversion device L ATU links to each other with contactor L BSB's first end again, and contactor L BSB's second end links to each other with busbar L115 VAC Bus.

Busbar R235 VAC Bus links to each other with contactor R ATUC's first end, and contactor R ATUC's second end links to each other with electric energy conversion device R ATU, and electric energy conversion device R ATU links to each other with contactor R BSB's first end again, and contactor R BSB's second end links to each other with busbar R115 VAC Bus.

Ground power source L FWD EP is connected to a first terminal of contact L EPC, and a second terminal of contact L EPC is connected to a first terminal of contact L BSB.

A ground power source R FWD EP is connected to a first terminal of the contact R EPC, and a second terminal of the contact R EPC is connected to a first terminal of the contact R BSB.

bus bar L235 VAC Bus is connected with the first end of contactor LacT, and the second end of contactor LacT is connected with the first end of contactor RacT, and the second end of contactor RacT is connected with Bus bar R235 VAC Bus.

The second end of contactor L ATUC is connected to the first end of contactor L TRU Rly, and the second end of contactor L TRU Rly is connected to power conversion device TRU L, and power conversion device TRU L is connected to busbar L28 VDC Bus again.

The second end of contactor R ATUC links to each other with the first end of contactor R TRU Rly, and the second end of contactor R TRU Rly links to each other with power conversion device TRU R, and power conversion device TRU R links to each other with busbar R28 VDC Bus again.

bus bar L28 VDC Bus is connected to a first terminal of contact LdcT, a second terminal of contact LdcT is connected to a first terminal of contact RdcT, and a second terminal of contact RdcT is connected to Bus bar R28 VDC Bus.

The second end of the contactor L ATUC is connected to the first end of the contactor E1 TRU ISO Rly, the second end of the contactor E1 TRU ISO Rly is connected to the first ends of the power conversion device TRU E1 and the contactor E1 TRU Rly, respectively, the power conversion device TRU E1 is connected to the first end of the Bus bar ESS 128 VDC Bus, the second end of the contactor ESS ISO Rly is connected to the Bus bar ESS 235VAC Bus, the Bus bar ESS 235VAC Bus is connected to the power conversion device TRU 2, and the power conversion device TRU E2 is connected to the Bus bar ESS 228 VDC Bus.

The generator GEN RAT is connected to a first terminal of a contactor RCB, a second terminal of which is connected to a Bus bar ESS 235VAC Bus.

The Bus ESS 128 VDC Bus is connected to the first terminal of the contact E1T, the second terminal of the contact E1T is connected to the first terminal of the contact E2T, and the second terminal of the contact E2T is connected to the Bus ESS 228 VDC Bus.

Bus ESS 128 VDC Bus is connected to a first terminal of contactor MBR, and a second terminal of contactor MBR is connected to Bus Hot BB 1.

busbar Hot BB2 links to each other with contactor SPUC's first end, and contactor SPUC's second end links to each other with the SPU, and the SPU links to each other with contactor SPUB's first end, and contactor SPUB's second end links to each other with self-coupling transformer rectifier ATRU R.

The Bus bar L235 VAC Bus is connected with the first end of the contactor L ATRUC, the second end of the contactor L ATRUC is connected with the autotransformer rectifier ATRU L, and the autotransformer rectifier ATRU L is connected with the Bus bar L270 VDC Bus.

The Bus bar R235 VAC Bus is connected with the first end of the contactor R ATRUC, the second end of the contactor R ATRUC is connected with the autotransformer rectifier ATRU R, and the autotransformer rectifier ATRU R is connected with the Bus bar R270 VDC Bus.

an external power source L AFT EP is connected with a first end of a contactor L AEPC, and a second end of the contactor L AEPC is connected with an autotransformer rectifier ATRU L.

under the multi-electric airplane architecture, unexpected parallel connection of a plurality of generators is prevented so as to prevent the generators from being damaged. For example, accidental closing of the connecting bus bar contactor may cause multiple generators to operate in Parallel, which is also referred to as a Sustained Parallel power Source (SPS) condition.

unexpected parallel conditions can cause many hazards, such as beat frequency, and two parallel generators, one of which is used as the load of the other, operate in the working mode of the motor and continuously consume power instead of outputting power, thereby causing the generators to be damaged.

Continuous unarmed power Source Protection (SUSP) is usually determined by detecting the reactive output of a generator, which normally has an upper limit, and when a SUSP condition occurs, a generator may draw excessive reactive power, and the GCU may determine whether the SUSP condition occurs by detecting whether the reactive power output of the generator exceeds a threshold.

The power factor of a normal generator lags by 0.85, resulting in a reduction in power factor as the reactive power output increases. When the power factor drops below 0.8, a persistent unfinished power source is considered to be present, i.e., the SPS condition is satisfied, and the GCU will implement protection after a delay of 2 s.

the protection control logic for a continuous unfixed power source is shown in fig. 4.

the foregoing merely represents embodiments of the present invention, which are described in some detail and detail, and therefore should not be construed as limiting the scope of the invention. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the inventive concept, which falls within the scope of the present invention. Therefore, the protection scope of the present patent shall be subject to the appended claims.