Sub-orbital vehicle and load aircraft combined power supply and distribution system

Abstract

The invention relates to a suborbital vehicle and load aircraft combined power supply and distribution system. The suborbital vehicle and the load aircraft share one set of distributor, and a suborbital vehicle power supply or a ground power supply is used for power supply in the launching preparation stage. The load power supply is activated before launching, a power supply loop of the suborbital vehicle and the load aircraft is closed after successful activation, and the load power supply directly supplies power to the load aircraft without secondary power distribution of a power distributor. The load power supply provides acquisition voltage output for external equipment to monitor, and no power supply and distribution switching exists in the separation process of the load aircraft and the sub-orbital vehicle. And the flight control machine and the sub-orbital vehicle distributor are jointly controlled by initiating explosive device actions. The method is simple and clear in principle, effectively reduces the space, weight and cost of the load aircraft, enhances the driving control capability of the initiating explosive device, and has remarkable practicability for the small-size load aircraft.

Description

Technical Field

[0001] The present invention relates to a power supply and distribution system for a suborbital carrier and a payload aircraft, belonging to the technical field of spacecraft power distribution. Background Art

[0002] The suborbital carrier is used to provide transportation services for the suborbital payload aircraft. After the suborbital carrier combination flies to a predetermined altitude, the payload aircraft separates from the carrier, and the payload aircraft flies and operates independently. The power supply and distribution system for the suborbital carrier and the payload aircraft is usually realized by two methods: (1) The suborbital carrier and the payload aircraft adopt independent power supply and distribution methods. The carrier distributor supplies power to the carrier equipment and controls pyrotechnics, and the payload aircraft distributor supplies power to the payload aircraft equipment. (2) The payload aircraft distributor provides power distribution and pyrotechnics control for the suborbital carrier and the payload aircraft.

[0003] The deficiencies of the above methods are as follows: 1) The independent power supply equipment is complex and costly; 2) It is not applicable when the small-sized payload aircraft has limited space and cannot accommodate the distributor; 3) When the distributor is located on the payload aircraft, it is not convenient to control pyrotechnics at the moment when the payload aircraft separates from the carrier. Summary of the Invention

[0004] The technical problem solved by the present invention: Overcoming the deficiencies of the prior art, a combined power supply and distribution system for a suborbital carrier and a payload aircraft is proposed to solve the problems of large space occupation, complex system, high cost, and inconvenient pyrotechnics control in the existing power supply and distribution system for a suborbital carrier and a payload aircraft.

[0005] The technical solution of the present invention is as follows:

[0006] On the one hand, the present invention proposes a combined power supply and distribution system for a suborbital carrier and a payload aircraft, including: a flight control computer, a payload power supply, a carrier distributor, and a carrier main power supply; the flight control computer and the payload power supply are arranged on the side of the payload aircraft, and the carrier distributor and the carrier main power supply are arranged on the side of the suborbital carrier;

[0007] The flight control computer serves as a control center to perform flight control for the suborbital carrier; after the payload aircraft separates from the suborbital carrier, the flight control computer provides flight control for the payload aircraft; the payload power supply is used to provide control power and servo power for the payload aircraft; the flight control computer monitors the power supply information of the payload aircraft and the suborbital carrier;

[0008] The payload aircraft and the suborbital carrier share the carrier distributor for power distribution control, use the carrier main power supply or the ground power supply to supply power to the carrier equipment, provide controllable power supply and pyrotechnics power for the payload aircraft, and perform joint pyrotechnics control with the flight control computer.

[0009] Furthermore, during the launch preparation phase, the main power supply of the suborbital carrier or the ground power supply is used. The payload power supply is activated before launch. After the successful activation of the payload power supply, the power supply circuits between the suborbital carrier and the payload aircraft are turned off.

[0010] After the activation of the payload power supply, it directly supplies power to the payload aircraft without secondary power distribution through a distributor. The payload power supply provides a sampling voltage for external equipment monitoring, and there is no power supply and distribution switching during the separation process of the payload aircraft and the suborbital carrier.

[0011] Furthermore, the payload power supply includes a payload battery and an anti-backflow diode.

[0012] The anti-backflow diode is set at the connection of the payload battery and the controllable power supply path of the carrier. After the activation of the payload battery, it has no impact on the main power supply of the carrier or the ground power supply. After the power supply is stable, the controllable power supply is turned off, and the power transfer and switching are completed. The power supply circuit between the carrier and the payload power supply is cut off. Thereafter, there is no power distribution switching during the separation process of the carrier and the payload aircraft.

[0013] Furthermore, the payload power supply is designed with a voltage sampling and output function. The output of the payload power supply is monitored through the sampling equipment of the payload aircraft or the carrier, which is used for real-time monitoring and launch control judgment of the launch control system.

[0014] Furthermore, the payload power supply uses a thermal battery, and the main power supply of the carrier uses a lithium battery or a thermal battery.

[0015] Furthermore, if the main power supply of the carrier uses a lithium battery, after entering the launch process, the carrier and the payload aircraft are powered by the main power supply without the need for ground power supply. Only the launch pad / rack is retained to cooperate with the wireless launch control system to complete wireless launch control.

[0016] If the main power supply of the carrier uses a thermal battery, after entering the launch process, the main power supply of the carrier needs to be activated first. After completing the power transfer between the carrier and the ground, the ground power supply is cut off. After the normal activation of the main power supply, the payload power supply is activated to complete the power transfer between the carrier and the payload aircraft.

[0017] Furthermore, according to the predetermined flight timing sequence, the flight control computer sends commands to the carrier distributor, and the distributor completes the actuation of the pyrotechnic devices.

[0018] Furthermore, the combined power supply and distribution system includes a formal launch mode and a test mode. In the formal launch mode, the main power supply of the carrier is used to provide electrical energy for the carrier and the payload aircraft. In the test mode, the ground power supply is used to provide electrical energy for the carrier and the payload aircraft. In the formal launch mode, the pyrotechnic device power supply is connected, and in the test mode, the pyrotechnic device power supply is not connected.

[0019] On the other hand, the present invention also proposes a combined power supply and distribution method implemented based on the combined power supply and distribution system of the carrier and the payload aircraft, including:

[0020] (1) Select the working mode of the combined power supply and distribution system. The combined power supply and distribution system includes a formal launch mode and a test mode. In the formal launch mode, the main power supply of the carrier is used to supply power to the carrier and the payload aircraft. In the test mode, the ground power supply is used to supply power to the carrier and the payload aircraft. In the formal launch mode, the pyrotechnic power supply is connected, and in the test mode, the pyrotechnic power supply is not connected.

[0021] (2) According to the launch timing sequence, activate the payload power supply. The payload battery information is collected by the flight control computer and then sent down. After the payload power supply is successfully activated and meets the power transfer requirements, the carrier distributor closes the controllable power supply circuit provided for the payload aircraft. If the power transfer requirements are not met, perform a power-off operation.

[0022] (3) After power transfer, the carrier equipment is powered by the main power supply of the carrier, and the payload aircraft is powered by the payload power supply. After the combined body of the carrier and the aircraft reaches the separation window, the carrier distributor drives the separation connector to separate. After confirming the separation of the separation connector, the carrier distributor performs the separation pyrotechnic operation. The payload aircraft flies independently and completes the mission.

[0023] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0024] (1) The principle of the combined power supply and distribution system of the present invention is clear, effectively reducing the space, weight, and cost of the payload aircraft, and having significant practicality for small-sized payload aircraft.

[0025] (2) The power supply structure of the combined power supply and distribution system of the present invention is simple, and it does not depend on the ground power supply during the launch process, increasing the launch convenience and reliability.

[0026] (3) The distributor of the combined power supply and distribution system of the present invention is located on the carrier, and the separation pyrotechnics drive does not need to pass through the separation connector, enhancing the pyrotechnics control ability during the separation process and reducing the separation risk. Brief Description of the Drawings

[0027] Figure 1 It is a schematic diagram of the composition of the combined power supply and distribution system of the present invention;

[0028] Figure 2 It is a schematic diagram of the interior of the payload power supply of the present invention;

[0029] Figure 3 It is the power-on timing diagram of the entire system of the present invention. Detailed Embodiment

[0030] As Figure 1 shown, the present invention provides a combined power supply and distribution system for a suborbital carrier and a payload aircraft, including: a flight control computer, a payload power supply, a carrier distributor, a main power supply of the carrier, and other aircraft electrical equipment.

[0031] The flight control computer serves as the control center to conduct flight control for the suborbital carrier; after the payload vehicle separates from the suborbital carrier, the flight control computer provides flight control for the payload vehicle; the flight control computer is also used to monitor the power supply information of the payload vehicle and the suborbital carrier.

[0032] The payload power supply is used to provide control power and servo power for the payload vehicle.

[0033] The main power supply of the carrier provides power supply for the suborbital carrier equipment through the carrier distributor, provides controllable power supply and pyrotechnic device power for the payload vehicle, and conducts joint control of pyrotechnic devices with the flight control computer.

[0034] The suborbital carrier and the payload vehicle share a set of distributors. During the launch preparation stage, the power supply of the suborbital carrier (or ground power supply) is used. The payload power supply is activated before launch. After successful activation, the power supply circuits of the suborbital carrier and the payload vehicle are closed. After the payload power supply is activated, it directly powers the payload vehicle without secondary power distribution through the distributor. The payload power supply provides the collected voltage for external equipment to monitor. There is no power supply and distribution switching during the separation process of the payload vehicle and the suborbital carrier. The flight control computer and the suborbital carrier distributor conduct joint control of pyrotechnic device actions.

[0035] The flight control computer sends pyrotechnic device drive instructions such as payload power supply activation instructions, carrier engine ignition instructions, and separation instructions of the payload vehicle and the carrier to the carrier distributor. At the same time, the flight control computer can collect or receive the payload power supply signals collected by other equipment to achieve real-time monitoring of the payload power supply.

[0036] The payload power supply generally selects a thermal battery. The power supply circuits of the main power supply of the suborbital carrier and the ground power supply converge inside the payload power supply and then supply power to the remaining equipment. A diode is used to implement the anti-backflow design to avoid the backflow impact on the main power supply after the payload power supply is activated.

[0037] As Figure 2 shown, the payload power supply includes a payload battery and an anti-backflow diode; the anti-backflow diode is set at the connection between the payload battery and the controllable power supply path of the carrier. After the payload battery is activated, it has no impact on the main power supply of the carrier or the ground power supply; after the power supply is stable, the controllable power supply is turned off, and the power transfer and switching are completed. The power supply circuit between the carrier and the payload power supply is cut off. After that, there is no power distribution switching during the separation process of the carrier and the payload vehicle.

[0038] The payload power supply provides the collected voltage output for other equipment to collect and monitor.

[0039] The suborbital vehicle's power distributor can be connected to the main power supply and the ground power supply to provide power for the vehicle and the equipment of the payload aircraft. It has a controllable power supply output function to provide controllable power supply for the payload aircraft. The power distributor has the function of initiating explosive devices, and receives commands from the flight control computer to complete drives such as power activation, engine ignition, and separation explosive device activation.

[0040] The power distributor of this combined power supply and distribution system is located on the vehicle. The separation explosive device drive does not need to pass through the separation connector. During the separation process, the separation connector can be disconnected first, and then the separation explosive drive can be executed, increasing the separation reliability.

[0041] If the main power supply of the vehicle uses lithium batteries, after entering the launch process, the vehicle and the payload aircraft use the main power supply for power supply, without the need for ground power supply. Only the launch pad / stand is retained to cooperate with the wireless launch control system to complete wireless launch control;

[0042] If the main power supply of the vehicle uses thermal batteries, after entering the launch process, it is necessary to first activate the main power supply of the vehicle, cut off the ground power supply after completing the vehicle-ground power transfer, and after the main power supply is activated normally, activate the payload power supply to complete the power transfer between the vehicle and the payload aircraft.

[0043] As Figure 3 shown, the working process of the power distribution system proposed by the present invention is as follows:

[0044] Step 1

[0045] When the entire system is powered on, the formal launch process and the test process can be selected. The formal launch process uses the main power supply of the vehicle to provide electrical energy for the entire system, and the test process uses the ground power supply to provide electrical energy for the entire system. The explosive device power supply is connected in the formal process, and the explosive device power supply is not connected in the test process.

[0046] Step 2

[0047] According to the launch timing, complete the activation of the payload power supply. The battery information can be collected by the flight control computer and sent down. After the activation is successful and meets the power transfer requirements, the vehicle power distributor closes the controllable power supply circuit provided for the payload aircraft; if the power transfer requirements are not met, enter the power-off process.

[0048] Step 3

[0049] Two parallel redundant diodes are designed in the circuit of the payload power supply and the power distributor to suppress the current of the payload power supply from entering the main power supply of the vehicle and realize the function of preventing power from flowing back. During the time interval between the activation of the payload power supply and the disconnection of the controllable power supply by the power distributor, the payload power supply will not affect the main power supply of the vehicle.

[0050] Step 4

[0051] After power transfer, the single equipment of the carrier uses the main power supply of the carrier, and the payload aircraft uses the payload power supply. After the carrier assembly reaches the separation window, the carrier distributor drives the separation connector to separate. After confirming the separation of the connector, the distributor performs the separation pyrotechnic operation. The payload aircraft flies independently and completes the mission.

[0052] The principle of the present invention is simple and clear, effectively reducing the space, weight and cost of the payload aircraft, enhancing the driving and control ability of pyrotechnics, and having remarkable practicability for small-sized payload aircraft.

[0053] The content not described in detail in the present invention is well-known technology to those skilled in the art.

Claims

1. A combined power supply and distribution system for a suborbital carrier and a payload aircraft, characterized in that Comprising: Flight control computer, payload power supply, vehicle distributor, vehicle main power supply; the flight control computer and the payload power supply are arranged on the payload aircraft side, and the vehicle distributor and the vehicle main power supply are arranged on the suborbital vehicle side; The flight control computer serves as the control center to conduct flight control for the suborbital vehicle; after the payload aircraft separates from the suborbital vehicle, the flight control computer provides flight control for the payload aircraft; the payload power supply is used to provide control power and servo power for the payload aircraft; the flight control computer monitors the power supply information of the payload aircraft and the suborbital vehicle; The payload aircraft and the suborbital vehicle share the vehicle distributor for power distribution control, use the vehicle main power supply or the ground power supply to supply power to the vehicle equipment, provide controllable power supply and pyrotechnic device power for the payload aircraft, and conduct joint control of pyrotechnic devices with the flight control computer.

2. The combined power supply and distribution system for a suborbital carrier and a payload aircraft according to claim 1, wherein: During the launch preparation stage, the suborbital vehicle main power supply or the ground power supply is used, the payload power supply is activated before launch, and after the payload power supply is successfully activated, the power supply circuits of the suborbital vehicle and the payload aircraft are closed; After the payload power supply is activated, it directly supplies power to the payload aircraft without secondary power distribution through the distributor. The payload power supply provides the collected voltage for external equipment monitoring, and there is no power supply and distribution switching during the separation process of the payload aircraft and the suborbital vehicle.

3. A combined power supply and distribution system for a suborbital carrier and a payload aircraft according to claim 1, characterized in that: The payload power supply includes a payload battery and an anti-backflow diode; The anti-backflow diode is arranged at the connection of the payload battery and the controllable power supply path of the vehicle. After the payload battery is activated, it has no impact on the vehicle main power supply or the ground power supply; after the power supply is stable, the controllable power supply is turned off, the power transfer switching is completed, and the power supply circuit between the vehicle and the payload power supply is cut off. Thereafter, there is no power distribution switching during the separation process of the vehicle and the payload aircraft.

4. A combined power supply and distribution system for a carrier and a payload aircraft, as described in claim 3, characterized in that: The payload power supply is designed with a voltage acquisition and output function, and the output of the payload power supply is monitored through the acquisition equipment of the payload aircraft or the vehicle, which is used for real-time monitoring and launch control judgment of the launch control system.

5. A combined power supply and distribution system for a carrier and a payload aircraft, as described in claim 1, characterized in that: The payload power supply uses a thermal battery, and the vehicle main power supply uses a lithium battery or a thermal battery.

6. The joint power supply and distribution system for a carrier and a payload aircraft according to claim 5, characterized in that: If the vehicle main power supply uses a lithium battery, after entering the launch process, the vehicle and the payload aircraft use the main power supply for power supply, without the need for ground power supply, and only the launch pad / rack is retained to complete wireless launch control in cooperation with the wireless launch control system; If the vehicle main power supply uses a thermal battery, after entering the launch process, it is necessary to first activate the vehicle main power supply, cut off the ground power supply after completing the vehicle-ground power transfer, and after the main power supply is normally activated, activate the payload power supply to complete the power transfer between the vehicle and the payload aircraft.

7. A combined power supply and distribution system for a carrier and a payload aircraft, characterized in that: According to the predetermined flight timing, the flight control computer sends commands to the vehicle distributor, and the distributor completes the driving of pyrotechnic devices.

8. A combined power supply and distribution system for a carrier and a payload aircraft, characterized in that: The joint power supply and distribution system includes a formal launch mode and a test mode. In the formal launch mode, the vehicle main power supply is used to provide electrical energy for the vehicle and the payload aircraft; in the test mode, the ground power supply is used to provide electrical energy for the vehicle and the payload aircraft; In the formal launch mode, the pyrotechnic device power supply is connected, and in the test mode, the pyrotechnic device power supply is not connected.

9. A combined power supply and distribution method implemented based on the combined power supply and distribution system of a carrier and a payload aircraft according to claim 1, characterized in that, Comprising: (1) Select the working mode of the joint power supply and distribution system. The joint power supply and distribution system includes a formal launch mode and a test mode. In the formal launch mode, the vehicle main power supply is used to provide electrical energy for the vehicle and the payload aircraft; in the test mode, the ground power supply is used to provide electrical energy for the vehicle and the payload aircraft; In the formal launch mode, the pyrotechnic power supply is connected, while in the test mode, the pyrotechnic power supply is not connected. (2) According to the launch timing sequence, complete the activation of the payload power supply. The payload battery information is collected by the flight control computer and then sent down. After the payload power supply is successfully activated and meets the power transfer requirements, the vehicle distributor closes the controllable power supply circuit provided for the payload aircraft; if the power transfer requirements are not met, perform a power-off operation. (3) After power transfer, the vehicle equipment is powered by the vehicle main power supply, and the payload aircraft is powered by the payload power supply; after the vehicle and aircraft combination reaches the separation window, the vehicle distributor drives the separation connector to separate. After confirming the separation of the separation connector, the vehicle distributor performs the separation pyrotechnic operation; the payload aircraft flies independently and completes the mission.

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