阅读说明：本技术 具有高入轨效率和强机动能力的飞行器及其入轨方法 (Aircraft with high rail-entering efficiency and strong maneuvering capability and rail-entering method thereof ) 是由 曹喜滨 王峰 韦常柱 李宁 于 2019-12-04 设计创作，主要内容包括：本发明实施例公开了一种具有高入轨效率和强机动能力的飞行器及其入轨方法,所述飞行器包括：固体发动机；连接至所述固体发动机的飞行器平台；以及安装至所述飞行器平台的载荷,所述载荷旨在随同所述飞行器飞行进入目标轨道以便执行任务；其中,所述固体发动机用于提供所述飞行器从地面发射场飞行进入亚轨道所需的飞行动力,其中,在所述飞行器飞行进入所述亚轨道之后,所述固体发动机从所述飞行器脱离,其中,所述飞行器平台中设置有液体推进系统,所述液体推进系统用于提供所述飞行器从所述亚轨道飞行进入所述目标轨道所需的飞行动力。(The embodiment of the invention discloses an aircraft with high rail entering efficiency and strong maneuverability and a rail entering method thereof, wherein the aircraft comprises: a solid state engine; an aircraft platform connected to the solid engine; and a load mounted to the aircraft platform, the load intended to fly with the aircraft into a target orbit for performing a task; wherein the solid engine is configured to provide the flight power required for the aircraft to fly from a ground launch site into a sub-orbit, wherein the solid engine is disengaged from the aircraft after the aircraft has flown into the sub-orbit, wherein a liquid propulsion system is disposed in the aircraft platform, the liquid propulsion system being configured to provide the flight power required for the aircraft to fly from the sub-orbit into the target orbit.)

1. An aircraft having high staging efficiency and enhanced maneuverability, comprising:

a solid state engine;

an aircraft platform connected to the solid engine; and

a load mounted to the aircraft platform, the load intended to fly with the aircraft into a target orbit for performing a mission;

wherein the solid state engine is used for providing the flight power required by the aircraft to fly from a ground launching field into a sub-orbit,

wherein the solid state engine is decoupled from the aircraft after the aircraft flies into the sub-orbit,

wherein a liquid propulsion system is arranged in the aircraft platform and is used for providing flight power required by the aircraft to fly from the sub-orbit into the target orbit.

2. The vehicle of claim 1, wherein the liquid propulsion system is further configured to provide flight power required for the vehicle to make at least one orbital transfer from the target trajectory to fly into a different mission trajectory.

3. The aircraft of claim 1, wherein the solids engine comprises at least one sub-stage engine that provides flight power to the aircraft in stages and each stage engine is decoupled from the aircraft after operation is complete.

4. The aircraft of claim 3 wherein the at least one substage engine is an existing solid state engine capable of rapid combined integration.

5. The aircraft of claim 1, wherein the load has a standardized interface adapted to the aircraft platform, the standardized interface enabling quick installation of the load to the aircraft platform.

6. The aircraft of claim 1 further comprising an on-board system that enables road transport and launch of the aircraft on the ground.

7. The aircraft of claim 1, wherein the amount of propellant remaining in the liquid propulsion system after the aircraft has flown into the target trajectory is more than 50% of the total amount of propellant.

8. The aircraft of claim 1 wherein the propellant employed in the liquid propulsion system is a bipropellant liquid propellant.

9. A method of staging an aircraft according to any one of claims 1 to 8, comprising:

flying the aircraft from a ground launch site into the sub-orbit by providing flight power through the solid state engine;

disengaging the solid engine from the aircraft after the aircraft flies into the sub-orbit;

after the solid engine is decoupled from the aircraft, providing flight power by the liquid propulsion system to fly the aircraft from the sub-orbit into the target orbit.

10. The method of claim 9, further comprising providing flight power by the liquid propulsion system to cause the aerial vehicle to make at least one orbital transfer from the target trajectory to fly into a different mission trajectory.

Technical Field

The invention relates to the field of aircrafts, in particular to an aircraft with high rail-entering efficiency and strong maneuverability and a rail-entering method thereof.

Background

The orbit entering efficiency of the aircraft is an important index which needs to be improved, and the orbit entering efficiency is the ratio of the maximum effective load mass which can be carried by the aircraft to the total takeoff mass of the aircraft under a specific task condition, and reflects the orbit entering capability of the aircraft under a specified condition.

The traditional approach to space load staging is to use a launch vehicle to directly deliver the payload to the intended orbit. Under the condition of a multi-stage in-orbit rocket, two or more than two substages are connected and work in sequence, the first substage of the multi-stage rocket is ignited to work and then pushes the whole rocket to accelerate to fly, the first substage rocket is separated from the whole rocket after working is finished, the second substage rocket is ignited to work and continues to push the rocket to fly, and the rest is done in sequence until the effective load is accelerated to a preset speed and sent to a preset track. In this case, for example, the last stage of the rocket needs to go through the entire flight from the launch until the entry into the predetermined trajectory together with the payload, and therefore the final stage is stiff (useless mass in the final stage, for example, the mass of the final stage housing other than the fuel of the final stage) and the rocket loses much of its carrying capacity, thereby affecting the efficiency of the entry.

Disclosure of Invention

In order to solve the above technical problems, embodiments of the present invention are expected to provide an aircraft with high rail entry efficiency and high maneuvering capability and a rail entry method thereof, which can greatly improve the rail entry efficiency of the aircraft, and enable the aircraft to have high maneuvering capability, that is, can more easily implement rail transfer.

The technical scheme of the invention is realized as follows:

in a first aspect, embodiments of the present invention provide an aircraft with high rail-entering efficiency and high maneuverability, the aircraft comprising:

a solid state engine;

an aircraft platform connected to the solid engine; and

a load mounted to the aircraft platform, the load intended to fly with the aircraft into a target orbit for performing a mission;

wherein the solid state engine is used for providing the flight power required by the aircraft to fly from a ground launching field into a sub-orbit,

wherein the solid state engine is decoupled from the aircraft after the aircraft flies into the sub-orbit,

wherein a liquid propulsion system is arranged in the aircraft platform and is used for providing flight power required by the aircraft to fly from the sub-orbit into the target orbit.

In a second aspect, embodiments of the present invention provide a method of staging an aircraft according to the first aspect, the method comprising:

flying the aircraft from a ground launch site into the sub-orbit by providing flight power through the solid state engine;

disengaging the solid engine from the aircraft after the aircraft flies into the sub-orbit;

after the solid engine is decoupled from the aircraft, providing flight power by the liquid propulsion system to fly the aircraft from the sub-orbit into the target orbit.

The embodiment of the invention provides an aircraft with high rail entering efficiency and strong maneuverability and a rail entering method thereof; after the aircraft enters the suborbit, the solid engine is separated from the aircraft, the aircraft finishes flying from the suborbit to the target orbit through the flying power provided by the liquid propulsion system arranged in the platform of the aircraft, so that the aircraft is not influenced by the stiffness of the carrier rocket from the suborbit, and the mass of the liquid propulsion system is far less than that of the solid engine providing the corresponding flying power, so that the orbit entering efficiency of the aircraft is greatly improved, the contradiction between the actual demand of the effective load and the insufficient carrying capacity is solved, and the maneuvering performance of the aircraft after the orbit entering can be realized through the liquid propulsion system, so that the aircraft has strong maneuvering capacity and can more easily realize orbit transfer.

Drawings

FIG. 1 is a schematic diagram of the components of an aircraft with high track-entering efficiency and high maneuverability according to an embodiment of the present invention;

fig. 2 is a schematic diagram of an entering process of an aircraft with high entering efficiency and strong maneuverability, provided by an embodiment of the present invention, wherein three dotted rings respectively represent a sub-track, a transition track and a target track;

fig. 3 is a schematic diagram of a method for staging an aircraft having high staging efficiency and high maneuverability according to an embodiment of the present invention.

Detailed Description

The technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.

Referring to fig. 1 and 2, an embodiment of the present invention provides an aircraft 100 with high rail-in efficiency and high maneuverability, the aircraft 100 comprising:

a solid engine 110;

an aircraft platform 120 connected to the solid engine 110; and

a load 130 mounted to the aircraft platform 120, the load 130 intended to fly with the aircraft 100 into a target orbit O3 for performing a mission;

wherein the solid state engine 110 is configured to provide the flight power required for the aircraft 100 to fly from the ground launch site GS into the sub-orbital O1,

wherein, after the aircraft 100 flies into the sub-orbital O1, the solid state engines 110 are detached from the aircraft 100,

wherein the aircraft platform 120 is provided therein with a liquid propulsion system 121, the liquid propulsion system 121 being configured to provide the flight power required for the aircraft 100 to fly from the sub-orbit O1 into the target orbit O3.

After the aircraft 100 enters the sub-orbit O1, the solid engine 110 is detached from the aircraft 100, the aircraft 100 completes the flight from the sub-orbit O1 to the target orbit O3 by the flight power provided by the liquid propulsion system 121 arranged in the aircraft platform 120, so that the aircraft 100 is not affected by the dead weight of the carrier rocket from the sub-orbit O1 as in the conventional approach of entering the orbit, and the liquid propulsion system 121 has much less mass than the solid engine providing the corresponding flight power, so that the carrying capacity is not lost much, the efficiency of entering the aircraft 100 is greatly improved, and the maneuvering performance of the aircraft 100 after entering the orbit can be realized by the liquid propulsion system 121, so that the aircraft 100 has strong maneuvering capability and can realize the orbit change more easily.

With respect to the above-mentioned aircraft 100, in the preferred embodiment of the present invention, the liquid propulsion system 121 can also provide the flight power required for the aircraft 100 to make at least one orbital transfer from the target orbit O3 to fly into different mission orbits, thereby achieving the powerful maneuvering capability of the aircraft 100.

With respect to the above-mentioned aircraft 100, in the preferred embodiment of the present invention, as shown in fig. 2, the process of the aircraft 100 flying from the sub-track O1 into the target track O3 includes flying from the sub-track O1 into the transition track O2 and flying from the transition track O2 into the target track O3. Specifically, taking the target track O3 as a track 500km from the ground as an example, the sub-track O1 may be a track 260km from the ground with an aircraft having a speed of 7.2km/s, and the transition track O2 may be a track 300km from the ground.

With respect to the above-described aircraft 100, in a preferred embodiment of the present invention, the aircraft 100 flies from the transition orbit O2 into the target orbit O3 in a transition manner of the huffman transfer. The Hoeman transfer refers to two impulse global optimum transfer with free time between coplanar circular orbits, wherein the orbits are double-cotangent ellipses respectively tangent with an outer circle and an inner circle at a far place and a near place.

With respect to the aircraft 100 described above, in a preferred embodiment of the present invention, as shown in fig. 1, the solid state engine 110 includes at least one sub-stage engine that provides flight power to the aircraft 100 in stages and each stage engine is disengaged from the aircraft 100 after the operation is completed. Specifically, as shown in fig. 1, the solid engine 110 may include three sub-engines 111, 112, 113, a first sub-engine 111 is ignited to propel the aircraft 100 to fly, the first sub-engine 111 is ignited to operate and then is disengaged from the aircraft 100, a second sub-engine 112 is ignited to operate to continue propelling the aircraft 100 to fly, and so on until a third sub-engine 113 sends the aircraft 100 to the sub-track O1.

With respect to the aircraft 100 described above, in a preferred embodiment of the present invention, the at least one sub-stage engine is an existing solid state engine capable of rapid combined integration,

with respect to the aircraft 100 described above, in a preferred embodiment of the present invention, the load 130 has a standardized interface (not shown) adapted to the aircraft platform 120, which enables a quick mounting of the load 130 to the aircraft platform 120.

With respect to the aircraft 100 described above, in a preferred embodiment of the present invention, the aircraft 100 further comprises an on-board system (not shown) that enables the aircraft 100 to be transported by road and launched on the ground, thereby enabling the aircraft 100 to be launched at a wider range of launch sites.

The standardized interface and the vehicle-mounted system can greatly improve the survival capability and the task adaptability of the aircraft, and have great significance for the development of the space technology.

With respect to the aircraft 100 described above, in a preferred embodiment of the present invention, the amount of propellant remaining in the liquid propulsion system 121 after the aircraft 100 enters the target trajectory O3 is more than 50% of the total amount of propellant. Taking the total weight of the aircraft platform 120 as 1000kg as an example, the liquid propulsion system 121 may carry 500kg of propellant, 160kg of propellant is consumed when the aircraft 100 enters the transition track O2 from the sub-track O1, 40kg of propellant is consumed when the aircraft 100 enters the target track O3 from the transition track O2, and at this time, 300kg of propellant still remains in the liquid propulsion system 121, accounting for 60% of the total amount of propellant, so that the aircraft 100 can enter a new operation track through one or at least one orbital transfer to meet different task requirements according to the on-orbit task requirements by using the remaining 300kg of propellant.

With respect to the aircraft 100 described above, in a preferred embodiment of the present invention, the propellant used in the liquid propulsion system 121 is a two-component liquid propellant. Wherein the bipropellant liquid propellant is a propellant composed of two components of liquid fuel and liquid oxidizer stored respectively.

An embodiment of the present invention further provides a method for bringing the aircraft 100 into orbit, where the method includes:

s301: flying the aircraft 100 from the ground launch site GS into the sub-orbit O1 by providing flight power through the solid state engines 110;

s302: disengaging the solid engine 110 from the aircraft 100 after the aircraft 100 flies into the sub-orbital O1;

s303: after the solid engine 110 is disengaged from the aircraft 100, flight power is provided by the liquid propulsion system 121 to fly the aircraft 100 from the sub-orbit O1 into the target orbit O3.

With respect to the above method, in a preferred embodiment of the present invention, the method further comprises providing flight power by the liquid propulsion system 121 to make the aircraft 100 perform at least one orbital transfer starting from the target orbit O3 to fly into a different mission orbit.

It should be noted that: the technical schemes described in the embodiments of the present invention can be combined arbitrarily without conflict.

The above description is only for the specific embodiments of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present invention, and all the changes or substitutions should be covered within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.