CN117922842A - Device and arrow integrated overall system of space station freight system - Google Patents

Abstract

The invention discloses a device and rocket integrated overall system of a space station freight system, which comprises a lifting type repeatedly-used freight aircraft and a repeatedly-used rocket, wherein the lifting type repeatedly-used freight aircraft adopts a tailless wing body assembly pneumatic layout and has the capabilities of repeated use, autonomous and rapid butt joint with the space station and loading of pressurized cargoes. The invention aims to overcome the defects of the existing space station freight system, and provides a device and arrow integrated overall system of the space station freight system, which realizes equipment resource sharing and sharing through the reusable and device and arrow integrated design of the system, reduces the number of equipment on the ground and the device, reduces the weight and power consumption requirements of the whole system, and greatly improves the ascending and descending capability of the space station freight transportation and the system reliability.

Description

Device and arrow integrated overall system of space station freight system

Technical Field

The application relates to the technical field of model population, in particular to a rocket-vessel integrated population system of a space station freight transport system.

Background

Along with the on-orbit assembly of the T-shaped configuration of the space station in China, the on-orbit construction of the space station in the heaven is finished in China, the application and development stages are entered, and the normalized operation is started. The novel freight aircraft with integrated aircraft and arrow is developed by adopting a differentiation technology route, so that the operation service style and means of space stations in China can be well supplemented, and the overall operation efficiency of the space stations in China can be remarkably improved.

Disclosure of Invention

The invention aims to overcome the defects of the existing space station freight system, and provides a device and arrow integrated overall system of the space station freight system, which realizes equipment resource sharing and sharing through the reusable and device and arrow integrated design of the system, reduces the number of equipment on the ground and the device, reduces the weight and power consumption requirements of the whole system, and greatly improves the ascending and descending capability of the space station freight transportation and the system reliability.

In a first aspect, an integrated rocket and aircraft system of a space station freight system is provided, which comprises a lift type reusable freight aircraft and a reusable rocket, wherein the lift type reusable freight aircraft adopts a tailless wing body assembly aerodynamic layout, and has the capabilities of repeated use, autonomous and rapid docking with a space station and loading of pressurized cargoes.

With reference to the first aspect, in certain implementations of the first aspect, the reusable rocket includes a reusable rocket first sub-stage and a non-reusable non-rocket second sub-stage mounted on the reusable rocket first sub-stage by a non-reusable inter-stage section.

With reference to the first aspect, in certain implementations of the first aspect, the actions of the system include:

The lift type reusable freight aircraft is launched through the first rocket sub-stage and the second rocket sub-stage, and after the first rocket sub-stage and the second rocket sub-stage are separated, the lift type reusable freight aircraft is pushed and launched into an initial orbit by the second rocket sub-stage without a fairing;

the lift type reusable freight aircraft is independently maneuvered to a space station running track through self auxiliary power;

The lift type reusable freight aircraft is remotely guided and independently controlled in a close range through the intersection butt joint and finally is in butt joint with a forward or backward butt joint port of a space station on the intersection track of the space station;

After the lift type repeatedly-used freight aircraft completes the running task of the on-orbit assembly, the lift type freight aircraft is separated from the space station and is autonomously controlled to a safe distance;

The lift type reusable freight aircraft is evacuated to a return track to finish the discharge of the residual propellant, off-track braking and reentry into the atmosphere, and the aircraft can accurately land on an airport runway.

With reference to the first aspect, in certain implementation manners of the first aspect, the lithium ion battery pack and the power distributor are installed on a lifting type reusable cargo aircraft, so that power supply and distribution are performed not only for self equipment of the lifting type reusable cargo aircraft, but also for rocket secondary stages.

With reference to the first aspect, in some implementations of the first aspect, the integrated electronic and measurement and control communication related devices are installed on a lift type reusable cargo aircraft, a non-electrical contact and a data bus interface exist between the reusable cargo aircraft and a rocket secondary, the lift type reusable cargo aircraft is connected with the rocket secondary through a TTE bus, and flight control, timing control, task management, initiating explosive device control, and measurement parameter acquisition and transmission of the reusable cargo aircraft and the rocket secondary are realized through the devices on the lift type reusable cargo aircraft.

With reference to the first aspect, in certain implementations of the first aspect, a lift-type reusable cargo aircraft is used to provide torque required for roll control for the rocket secondary.

With reference to the first aspect, in some implementations of the first aspect, a YF-100MI liquid oxygen kerosene engine with vacuum thrust 1434kN is installed at the rocket secondary stage, and the engine swings to provide control moment in pitch and yaw directions, the maximum synthetic swing angle is 1.8 °, and the rolling interference moment generated by the engine in operation is 6757Nm.

With reference to the first aspect, in certain implementations of the first aspect, the ascending section of the lift-type reusable cargo aircraft provides the control torque required for the roll direction by means of 8 1000N RCS engines mounted on the trailing end face.

With reference to the first aspect, in certain implementations of the first aspect, the 8 1000N RCS engine operates to provide a control torque of 7534Nm.

In a second aspect, a method for applying an integrated system of space station freight systems is provided, the method comprising:

The lift type reusable freight aircraft is pushed to launch into a track by a reusable rocket without a fairing;

the lift type reusable freight aircraft is independently maneuvered to a space station running track through self auxiliary power;

The lift type reusable freight aircraft is remotely guided and independently controlled in a close range through the intersection butt joint and finally is in butt joint with a forward or backward butt joint port of a space station on the intersection track of the space station;

after the lift type reusable freight aircraft completes the running task of the on-orbit assembly, the lift type reusable freight aircraft is separated from the space station and is autonomously controlled to a safe distance;

The lift type reusable freight aircraft is evacuated to a return track to finish the discharge of the residual propellant, off-track braking and reentry into the atmosphere, and the aircraft can accurately land on an airport runway.

Compared with the prior art, the scheme provided by the application at least comprises the following beneficial technical effects:

(1) The novel lifting type aircraft structure is adopted, so that the control stability of the aircraft can be greatly improved, and the requirement of large-range change of mass centers in the cargo transportation process is met; the design scheme of 'rocket integration' is adopted, the freight aircraft and the carrier rocket are designed in a two-level integrated manner, and a set of electrical equipment and a control system are shared, so that the development of an electrical system fusion technology is promoted; the overall device unifies health management, enabling "airlined" flights. Advanced technologies such as structure light weight, no cable, complete machine health management and the like are adopted, and an artificial intelligence technology is applied to flight planning and intelligent management, so that the comprehensive upgrading of the traditional spacecraft is realized, and a large number of new technological developments such as material, no cable, intelligent and the like can be driven.

(2) The present invention is different from the current space station service space boat, in combination with the experience of developing an aircraft, the lifting body pneumatic configuration with more return advantages is selected, and the complete landing multiplexing of the aircraft can be realized; the freight aircraft has 5 tons of cargo ascending and descending capability, and compared with the configuration of an airship, the freight aircraft returns more superior environmental conditions, the overload is not more than 2.5g, the freight aircraft can meet the cargo transportation with higher requirements, realizes the stable and comfortable return of high-value cargoes, can greatly improve the cargo descending capability of space stations in China, and meets the transportation requirements of increasingly diversified tasks of the space stations; the aircraft has strong descending capability, and provides conditions for the space station to develop large-scale space application by utilizing special space environments such as microgravity, high vacuum and the like, such as large-scale on-orbit manufacturing return, experimental sample return and the like.

(3) The invention adopts a new generation of reusable manned rocket to push the launching and the track entering without the fairing, thereby saving the launching fairing and reducing the system development cost; the carrier rocket and the reusable freight aircraft which are used repeatedly are adopted, the repeated use rate of the whole freight transportation system is higher, the number of disposable products is less, and only rocket supports and the simplified rocket are used once. The carrier rocket can be reused for 10 times, and the freight aircraft can be reused for 20 times, so that compared with a disposable freight transportation system, the carrier rocket has remarkable advantages in the aspects of service cost, test initiation period, re-launching time and the like, and a new technical approach is provided for realizing low-cost freight.

Drawings

Fig. 1 is a schematic diagram of a space station cargo system scheme of the present invention.

Fig. 2 is a cross-section of a space station freight system flight mission according to the present invention.

Fig. 3 is an electrical architecture diagram of the space station freight system of the invention.

Detailed Description

The application is described in further detail below with reference to the drawings and the specific embodiments.

Referring to fig. 1, an integrated rocket and aircraft system for a space station freight system according to an embodiment of the present application includes a lift-type reusable freight aircraft and a reusable rocket. The system may be launched by reusing rocket first sub-stages (not shown in FIG. 1) and rocket second sub-stages. The lifting type repeatedly-used freight aircraft (hereinafter referred to as lifting type freight aircraft) adopts the pneumatic layout of a tailless wing body assembly, and has the capabilities of repeated use, autonomous and rapid docking with a space station and loading 5t pressurized cargoes; the reusable rocket adopts a new generation human rocket CZ-10A which has been established in China.

The task section of the space station low-cost cargo transportation system is shown in fig. 2, and the main action procedures are as follows:

1) The lift type freight aircraft is pushed to launch and enter a track by a reusable rocket without a fairing, and is launched to an initial track with the height of about 200km multiplied by 340km (the height of a remote place is determined according to actual needs);

2) The vehicle is automatically moved to a space station running track through self auxiliary power;

3) The method comprises the steps of carrying out long-distance guidance and short-distance autonomous control through intersecting and butting, and finally butting with a space station forward or backward butting port on a space station intersecting track;

4) After the aircraft completes the running task of the on-orbit assembly, the lifting freight aircraft is separated from the space station and is autonomously controlled to a safe distance;

5) And (5) evacuating to a return track to finish the discharge of the residual propellant, off-track braking and re-entering the atmosphere, and accurately landing on an airport runway.

The space station low-cost cargo transportation system fully adopts an electric integrated design thought, the electric system architecture of the lifting type freight aircraft is shown in fig. 3, and the power supply and distribution of all equipment of the freight aircraft and a power cabin (a carrier rocket secondary stage) are mainly realized. The 28V and 270V lithium ion storage battery pack and the power distributor are arranged on the freight aircraft, so that power supply and distribution are performed for equipment of the freight aircraft, and power supply and distribution are performed for rocket secondary related equipment. The comprehensive electronic and measurement and control communication related equipment is arranged on the freight aircraft and is connected with the rocket secondary related equipment through a TTE bus, so that functions of flight control, time sequence control, task management, initiating explosive device control, measurement parameter acquisition, transmission and the like of the freight aircraft and the rocket secondary are realized. And only a servo manager, a steering engine and related products of a power system are installed at the rocket secondary stage. The interfaces such as non-electrical contacts and data buses exist between the freight aircraft and the secondary level of the carrier rocket, and the redundant weight is reduced and the repeated use rate of products such as power supply, comprehensive electricity and the like is improved through the optimal configuration of the freight aircraft and the secondary level of the carrier rocket. The launching ascending section adopts a conventional rocket guidance control method, and the freight aircraft carries out flight control on the rocket secondary after the rocket primary and the rocket secondary are separated.

The lift type freight aircraft in the ascending section mainly provides the moment required by rolling control for the secondary stage, a YF-100MI liquid oxygen kerosene engine with vacuum thrust of 1434kN is arranged on the secondary stage of the carrier rocket, the main engine can provide the control moment in the pitching and yawing directions after swinging, the maximum synthetic swinging angle is 1.8 degrees through analysis, and the rolling interference moment generated by the main engine during operation is about 6757Nm.

The lifting type freight aircraft ascending section provides control moment required by rolling direction by means of 8 1000N RCS engines arranged on the tail end face, and the control moment available for the 8 1000N RCS engines to work is about 7534Nm, so that the control capability is sufficient.

While the invention has been described in terms of the preferred embodiment, it is not intended to limit the invention, but it will be apparent to those skilled in the art that variations and modifications can be made without departing from the spirit and scope of the invention, and therefore the scope of the invention is defined in the appended claims.

Claims (10)

1. The utility model provides a ware arrow integration overall system of space station freight transportation system, its characterized in that includes lift formula repeatedly usable freight transportation aircraft and repeatedly usable rocket, and wherein, lift formula repeatedly usable freight transportation aircraft adopts tailless wing body assembly aerodynamic layout, possesses repetitious reuse, with space station autonomous quick docking, load pressurized cargo's ability.

2. The system of claim 1, wherein the reusable rocket includes a reusable rocket first sub-stage and a non-reusable non-rocket second sub-stage mounted on the reusable rocket first sub-stage by a non-reusable inter-stage section.

3. The system of claim 2, wherein the actions of the system comprise:

The lift type reusable freight aircraft is launched through the first rocket sub-stage and the second rocket sub-stage, and after the first rocket sub-stage and the second rocket sub-stage are separated, the lift type reusable freight aircraft is pushed and launched into an initial orbit by the second rocket sub-stage without a fairing;

the lift type reusable freight aircraft is independently maneuvered to a space station running track through self auxiliary power;

The lift type reusable freight aircraft is remotely guided and independently controlled in a close range through the intersection butt joint and finally is in butt joint with a forward or backward butt joint port of a space station on the intersection track of the space station;

After the lift type repeatedly-used freight aircraft completes the running task of the on-orbit assembly, the lift type freight aircraft is separated from the space station and is autonomously controlled to a safe distance;

The lift type reusable freight aircraft is evacuated to a return track to finish the discharge of the residual propellant, off-track braking and reentry into the atmosphere, and the aircraft can accurately land on an airport runway.

4. The system of claim 2, wherein the lithium ion battery and the power distributor are mounted on a lift-type reusable cargo aircraft for power supply and distribution not only to the lift-type reusable cargo aircraft's own equipment, but also to the rocket secondary.

5. The system of claim 2, wherein the integrated electronic and measurement and control communication related devices are both mounted on a lift type reusable cargo aircraft, wherein a non-electrical contact and a data bus interface exist between the reusable cargo aircraft and a rocket secondary, the lift type reusable cargo aircraft is connected with the rocket secondary through a TTE bus, and flight control, timing control, task management, initiating explosive device control, and measurement parameter acquisition and transmission of the reusable cargo aircraft and the rocket secondary are realized through the devices on the lift type reusable cargo aircraft.

6. The system of claim 2, wherein the lift-type reusable cargo aircraft is configured to provide torque required for roll control for the rocket secondary.

7. The system of claim 6 wherein the rocket secondary is equipped with a vacuum thrust 1434kN YF-100MI liquid oxygen kerosene engine, the engine rocking is used to provide pitch and yaw direction control torque, the maximum resultant rocking angle is 1.8 °, and the engine operating produces a roll disturbance torque of 6757Nm.

8. The system of claim 1, wherein the ascending section of the lift type reusable cargo aircraft provides the control torque required for the roll direction by means of 8 1000N RCS engines mounted on the trailing face.

9. The system of claim 8, wherein the 8 1000N RCS engine operates to provide a control torque of 7534Nm.

10. A method of using an integrated system for integrating a ship and an arrow in a space station cargo system, the method comprising:

The lift type reusable freight aircraft is pushed to launch into a track by a reusable rocket without a fairing;

the lift type reusable freight aircraft is independently maneuvered to a space station running track through self auxiliary power;

The lift type reusable freight aircraft is remotely guided and independently controlled in a close range through the intersection butt joint and finally is in butt joint with a forward or backward butt joint port of a space station on the intersection track of the space station;

after the lift type reusable freight aircraft completes the running task of the on-orbit assembly, the lift type reusable freight aircraft is separated from the space station and is autonomously controlled to a safe distance;

The lift type reusable freight aircraft is evacuated to a return track to finish the discharge of the residual propellant, off-track braking and reentry into the atmosphere, and the aircraft can accurately land on an airport runway.