Self-adaptive centroid propulsion and attitude and orbit control integrated power system

Abstract

The invention provides a self-adaptive centroid propelling and attitude and orbit control integrated power system, and belongs to the technical field of rocket power and aircraft control, the self-adaptive centroid propelling and attitude and orbit control integrated power system comprises a front mounting bracket, a rear mounting bracket, four fixed engines, a swing engine and a propellant supply system, and the four fixed engines with nozzles facing outwards in the radial direction are symmetrically mounted on the front mounting bracket in a cross shape; four swing engines with nozzles capable of being switched in the radial direction and the vertical radial direction are symmetrically installed on the rear installation support in a cross shape. The propellant supply system is installed on the front installation support and provides propellant for the fixed / swing engines. The front mounting bracket and the rear mounting bracket can move relatively to change the longitudinal centroid position of the aircraft, the jet pipe direction of the swinging engine is variable, and the propelling and attitude and orbit control integrated capability is realized, so that the mounting position of the orbit control engine is not limited by the longitudinal centroid position of the aircraft; and the problems of expenditure, cycle and technical maturity caused by newly researching a larger-thrust orbit control engine can be avoided.

Description

Technical Field

[0001] The present invention relates to an attitude and orbit control power system, in particular to an adaptive center of mass propulsion and attitude and orbit control integrated power system, which has both propulsion and attitude and orbit control functions and can greatly increase orbit control thrust and attitude control flexibility by force system synthesis, and belongs to the field of rocket power technology and aircraft control technology. Background Art

[0002] Attitude and orbit control propulsion systems are widely used in spacecraft such as probes, satellites, rockets, and missiles. Rocket engines installed at different positions on the spacecraft generate lateral thrust along the spacecraft to achieve rapid and large-scale attitude adjustments and flight trajectory / orbit maneuvers. However, in some specific scenarios, the existing attitude and orbit control propulsion systems cannot meet application requirements well. For example, after some aircraft are separated from the spacecraft / carrier / upper stage / mother cabin, they still need to provide acceleration along the axial / forward direction of the aircraft in order to enter the predetermined orbit. It is difficult to achieve this goal well by relying solely on the attitude and orbit control power system on the aircraft that can only generate lateral force. It is often necessary to install additional thrusters at the rear end of the aircraft, which leads to a significant increase in the longitudinal length and weight of the entire aircraft, and it is also necessary to consider issues such as safe separation and deorbiting of the thrusters. In order to improve the rapid maneuverability of the aircraft, it is often required to configure a high-thrust orbit control engine. However, in order to achieve energy optimization and take into account both high thrust and high specific impulse, the nozzle of the orbit control engine needs to have a large expansion ratio to ensure that the combustion products are fully expanded, which will lead to an increase in the size of the nozzle structure, and the weight and envelope size of the aircraft will exceed the design constraints. In an ideal state, the thrust action line of the orbit control engine should pass through the center of mass of the aircraft to avoid generating additional interference torque. For aircraft that fly for a long time, as the propellant is consumed, the center of mass of the aircraft changes significantly, but the thrust vector remains unchanged, which results in the torque formed by the thrust vector of the orbit control engine relative to the center of mass causing greater interference to flight control.

[0003] All traditional orbit control engines are designed to be symmetrically distributed in a plane perpendicular to the longitudinal axis of the vehicle and coinciding with the center of mass of the vehicle. As a result, when the thrust demand for orbit control engines for newly developed vehicles increases significantly, new orbit control engines can only be developed and mature products cannot be directly used, resulting in low maturity, increased development cycle and costs. In addition, when traditional attitude and orbit control engines operate in dense / thin atmosphere, the lateral jets of the attitude and orbit control engines and the atmospheric flow form complex side jet interference, which deteriorates the control accuracy and stability of the vehicle.

[0004] To sum up, there is still much room for improvement in the existing attitude and orbit control power system, and it needs to be improved in many aspects such as flexible diversity of functions, product reusability, and applicability to complex scenarios. Summary of the invention

[0005] In order to improve and enhance the function / performance of the existing attitude and orbit control power system, the present invention provides an adaptive center of mass propulsion and attitude and orbit control integrated power system.

[0006] An adaptive mass center propulsion and attitude and orbit control integrated power system, comprising a front mounting bracket, a rear mounting bracket, a fixed engine, a swing engine, and a propellant supply system; the propulsion and attitude and orbit control integrated power system is installed at the rear of an aircraft, and its longitudinal center axis coincides with the longitudinal center axis of the aircraft, and the front mounting bracket is located on one side of the aircraft's forward direction;

[0007] The front mounting bracket includes a front mounting plate and a front center frame. The longitudinal center axis of the front center frame coincides with the normal center axis of the front mounting plate. The front mounting plate is symmetrically distributed in a "cross" shape along the normal direction of the plate surface and has four mounting slots. A fixed engine is installed in each mounting slot, and the nozzle of the fixed engine points to the edge of the front mounting plate.

[0008] The rear mounting bracket comprises a rear mounting plate and a rear center frame, the longitudinal center axis of the rear center frame coincides with the normal center axis of the rear mounting plate surface, the rear mounting plate is symmetrically distributed in a "cross" shape along the normal direction of the plate surface and has four mounting slots, each of which is hingedly mounted with a swing engine, the swing engine being able to rotate around a hinge axis within a longitudinal symmetric plane of the mounting slot under the drive of a drive device, a limit locking structure is arranged along the radial and longitudinal directions of the mounting slot, the initial rotation of the swing engine is placed at a longitudinal limit position where the nozzle is directed perpendicular to the rear of the rear mounting plate surface; the swing engine is constrained and locked by a locking device that can be unlocked controllably, and after the swing engine is unlocked, it turns under the drive of the drive device, and rotates around the hinge axis within the longitudinal symmetric plane of the mounting slot to lock at a radial limit position where the nozzle is directed parallel to the rear mounting plate surface;

[0009] The "cross" center lines of the four installation slots located on the front installation plate and the "cross" center lines of the four installation slots located on the rear installation plate are mirror images of each other along a cross section perpendicular to the longitudinal center axis of the propulsion and attitude and orbit control integrated power system, and the thrust center lines of the fixed engine and the swing engine installed in the corresponding installation slots are coplanar;

[0010] The propellant supply system is installed on the front center frame, and the propellant supply system is connected with the propellant injection ports of the fixed engine and the swing engine through pipelines, solenoid valves, and one-way valves.

[0011] Furthermore, the propellant supply system includes a propellant tank and a high-pressure gas cylinder. The propellant tank and the high-pressure gas cylinder are installed on the outer wall of the front center frame. The high-pressure gas cylinder and the propellant tank are connected through a pipeline, a one-way valve, and an electromagnetic valve. The propellant tank is connected to the propellant injection ports of the fixed engine and the swing engine through the pipeline, the electromagnetic valve, and the one-way valve. The high-pressure gas cylinder contains high-pressure helium, and the propellant tank contains propellant. When the electromagnetic valve on the pipeline is opened, the high-pressure helium in the high-pressure gas cylinder enters the propellant tank, pressurizes the propellant and pushes it to the propellant injection ports of the fixed engine and the swing engine.

[0012] Furthermore, the integrated propulsion and attitude and orbit control power system also includes a spring and a detonating cord. The detonating cord serves as a locking device that can be unlocked controllably. The swing engine is rotated to place the nozzle in a longitudinal limit position perpendicular to the rear surface of the rear mounting disk. The detonating cord is wound along the circumferential direction of the rear mounting disk surface to constrain and lock the four swing engines. The spring serves as a driving device, one end of which is hung on the tail of the swing engine, and the other end is stretched radially along the rear mounting disk and hung on the bottom of its mounting groove, thereby forming a driving force that causes the swing engine to rotate around the hinge axis within the longitudinal symmetry plane of the mounting groove.

[0013] Furthermore, the swing engine has a rotating shaft symmetrically arranged along the radial outer wall of the combustion chamber, a pair of bearings are symmetrically arranged in the wall of the installation groove and in the longitudinal symmetry plane of the installation groove, and the swing engine is rotatably connected to the installation groove of the rear installation plate through the rotating shaft and the bearings.

[0014] Furthermore, the swing engine is rotated so that the nozzle is perpendicular to the rear mounting disk surface and locked in a rearward limit position. The swing engine is ignited for the propulsion of the aircraft. By adjusting the thrust or working time of the four fixed engines and the four swing engines, a torque is formed relative to the center of mass of the aircraft, and the aircraft attitude is controlled while propulsion is performed.

[0015] Furthermore, the fixed engine and the swing engine are rocket engines / gas generators using liquid fuel or gel fuel.

[0016] Furthermore, the propellants used by the fixed engine and the swing engine are monopropellants or bipropellants.

[0017] Furthermore, after the swing engine is unlocked, it turns under the drive of the driving device, rotates around the hinge axis in the longitudinal symmetry plane of the installation groove until the nozzle points to the radial limit position parallel to the surface of the rear installation disk and is locked, without actively changing the longitudinal position of the center of mass of the aircraft. The fixed engine and the swing engine with the same nozzle direction on the front installation disk and the rear installation disk are ignited and work at the same time, and the thrust of the aforementioned fixed engine and the swing engine are adjusted so that the thrust generated by the two engines is inversely proportional to their respective longitudinal distances from the center of mass of the aircraft. According to the principle of force synthesis, the line of action of the resultant force of the thrust generated by the fixed engine and the swing engine passes through the center of mass of the aircraft and is perpendicular to the longitudinal center axis of the aircraft. The resultant force is equal to the sum of the thrusts generated by the fixed engine and the swing engine, thereby realizing the orbit control action of the aircraft; the fixed engine and the swing engine are ignited separately or simultaneously to generate thrusts of different magnitudes / directions, which generate torque relative to the center of mass, thereby realizing the attitude control of the aircraft.

[0018] Furthermore, the front center frame and the rear center frame form a sliding pair capable of producing controlled relative movement, and the center of mass position of the aircraft is longitudinally located between the front mounting plate and the rear mounting plate, and changes longitudinally as the front center frame and the rear center frame slide relative to each other.

[0019] Furthermore, the front center frame is a columnar structure with a square cross section, and the rear center frame is a columnar structure with a square cross section. The front center frame and the rear center frame are coaxially sleeved and assembled along their longitudinal center axes.

[0020] Furthermore, a guide rail is provided between the front center frame and the rear center frame, and the front center frame slides relatively to the rear center frame in a controlled manner along the guide rail.

[0021] Furthermore, after the swing engine is unlocked, it turns under the drive of the driving device, rotates around the hinge axis in the longitudinal symmetry plane of the installation groove until the nozzle points to the radial limit position parallel to the surface of the rear installation disk and is locked. Through the relative controlled sliding of the front center frame and the rear center frame, the longitudinal position of the center of mass of the aircraft is actively changed, so that the distance between the center of mass of the aircraft and the front installation disk and the rear installation disk is inversely proportional to the thrust generated by the fixed engine and the swing engine with the same nozzle direction on the front installation disk and the rear installation disk. The corresponding engine is ignited to generate thrust. According to the principle of force synthesis, the line of action of the resultant force on the aircraft passes through the center of mass of the aircraft and is perpendicular to the longitudinal center axis of the aircraft. The magnitude of the resultant force is equal to the sum of the thrusts generated by the fixed engine and the swing engine, thereby realizing the orbit control action of the aircraft; the fixed engine and the swing engine are ignited separately or simultaneously to generate thrusts of different magnitudes / directions, which generate torque relative to the center of mass, thereby realizing the attitude control of the aircraft.

[0022] The beneficial technical effects achieved by the present invention are:

[0023] An adaptive center of mass propulsion and attitude and orbit control integrated power system is proposed. A swing engine with changeable thrust direction is used to perform propulsion and attitude and orbit control functions in a time-sharing manner, avoiding the addition of an independent propulsion stage system to the aircraft, and effectively reducing the structural mass and system design complexity caused by the addition of new tanks, pressurization systems, pipelines, etc.; the longitudinal position of the aircraft's center of mass is changed by the relative controlled sliding of the front center frame and the rear center frame, so that the installation position of the orbit control engine is no longer constrained by the longitudinal center of mass position of the aircraft, and the traditional introduction of dead weight such as increasing the balancing mass to make the thrust centerline of the orbit control engine pass through the center of mass of the aircraft is avoided; by changing the aircraft The longitudinal position of the center of mass or the thrust of the fixed engine and the swing engine in the same direction of the nozzle can be dynamically adjusted. The principle of force synthesis is used to make the resultant force equal to the sum of the thrusts of the fixed engine and the swing engine. The line of action of the resultant force always follows the movement of the center of mass during the flight of the aircraft. By synthesizing the thrust of the fixed engine and the swing engine in the same direction, more engines in the same direction can be further expanded for thrust synthesis, instead of the traditional method of newly developing larger orbit control engines. A single type of orbit control engine can meet greater orbit control thrust requirements, avoiding the funding, cycle and technical maturity issues brought about by newly developed larger thrust orbit control engines.

[0024] Other features and advantages of the present invention will be described in the following description, and partly become apparent from the description, or be understood by practicing the present invention. The purpose and other advantages of the present invention can be realized and obtained by the structures particularly pointed out in the written description, claims, and drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is a schematic diagram of the composition of the present invention;

[0026] Figure 2 It is a schematic diagram of assembling the front and rear mounting brackets of the present invention;

[0027] Figure 3 is a schematic diagram of the rear mounting bracket of the present invention;

[0028] Figure 4 is a top view of the initial state of the present invention;

[0029] Figure 5 It is a left view of the initial state of the present invention;

[0030] Figure 6 It is a front view of the initial state of the present invention;

[0031] Figure 7 It is a rear view of the initial state of the present invention;

[0032] Figure 8 It is a partial front view of the initial state of the rear mounting plate, the swing engine and the spring of the present invention;

[0033] Fig. 9 It is a partial front view of the rear mounting plate, the swing engine and the spring in the unfolded state of the present invention;

[0034] Fig.10 This is a rear view of the swing engine of the present invention in the deployed state;

[0035] Fig.11 This is a front view of the swing engine of the present invention in the deployed state;

[0036] Fig.12 It is a top view of the swing engine of the present invention in the unfolded state and the force action line adjustment state;

[0037] Fig.13 It is a left front side view of the swing engine of the present invention in the unfolded state and the force action line adjustment state.

[0038] Figure numerals: 1. front mounting bracket; 11. front mounting plate; 12. front center frame; 2. rear mounting bracket; 21. rear mounting plate; 22. rear center frame; 3. fixed engine; 4. swing engine; 5. propellant supply system; 51. propellant tank; 52. high-pressure gas cylinder; 6. spring; 7. detonating cord. DETAILED DESCRIPTION

[0039] The specific implementation of the present invention is further described below in conjunction with the accompanying drawings. It should be noted that the description of the implementation is only used to help understand the present invention, but does not constitute a limitation of the present invention. In addition, the technical features involved in the implementation of the present invention described below can be combined with each other as long as they do not conflict with each other, and any other additions, reductions, integrations, changes or other equivalent replacement methods that do not deviate from the technical solution of the present invention are included in the protection scope of the patent of the present invention.

[0040] like Figures 1 to 13 As shown, a specific embodiment of an integrated propulsion and attitude and orbit control power system with adaptive center of mass includes a front mounting bracket 1, a rear mounting bracket 2, a fixed engine 3, a swinging engine 4, a propellant supply system 5, a spring 6, and a detonating cord 7. According to the customary expression in the industry, the side facing the head during installation is the front, and the side opposite thereto is the rear. The front mounting bracket 1 includes a front mounting plate 11 and a front center frame 12. The rear mounting bracket 2 includes a rear mounting plate 21 and a rear center frame 22. The integrated propulsion and attitude and orbit control power system is installed at the rear of the aircraft, and its longitudinal center axis coincides with the longitudinal center axis of the aircraft, and the front mounting plate 11 is located on the side of the forward direction of the aircraft.

[0041] like Figure 1 , Figure 2 , Figure 4 , Figure 5 , Figure 6As shown, in this specific embodiment, the front center frame 12 is a columnar structure with a square cross-section. The longitudinal center axis of the front center frame 12 coincides with the normal center axis of the front mounting plate 11 to form a front mounting bracket 1, which is in a "T" shape when viewed from the side. The front mounting plate 11 has four mounting grooves symmetrically distributed in a "cross" shape along the normal direction of the plate surface. A fixed engine 3 is installed in each mounting groove, and the nozzle of the fixed engine 3 points to the edge of the front mounting plate 11.

[0042] like Figure 1 , Figure 2 , Figure 3 , Figure 7 , Figure 8 , Fig. 9 , Fig.10 , Fig.11 As shown, in this specific embodiment, the rear center frame 22 is a columnar structure with a square cross-section. The longitudinal center axis of the rear center frame 22 coincides with the normal center axis of the rear mounting plate 21 to form a rear mounting bracket 2, which is in a "T" shape when viewed from the side. The rear mounting plate 21 is symmetrically distributed in a "cross" shape along the normal direction of the plate surface, and has four mounting grooves, each of which is equipped with a swing engine 4. The swing engine 4 is symmetrically provided with a rotating shaft along the radial outer wall of the combustion chamber. A pair of bearings are symmetrically provided in the wall surface of the mounting groove and the longitudinal symmetric surface of the mounting groove. The swing engine 4 is rotatably connected to the mounting groove of the rear mounting plate 21 through the rotating shaft and the bearing. Then, the swing engine 4 can rotate around the rotation axis in the longitudinal symmetric plane of the installation groove, and the installation groove is provided with a limit locking structure in the radial and longitudinal directions. The swing engine 4 is initially rotated to place the nozzle in the longitudinal limit position perpendicular to the rear mounting plate 21 and backward. The detonating cord 7 is wound along the circumferential direction of the rear mounting plate 21 to constrain and lock the four swing engines 4. One end of the spring 6 is hung at the tail of the swing engine 4, and the other end is stretched radially along the rear mounting plate 21 and hung at the bottom of the mounting groove of the rear mounting plate 21. The spring 6 serves as a driving device to form a driving force to rotate the swing engine 6 around the rotation axis in the longitudinal symmetric plane of the installation groove. According to actual needs, the driving device can also be in other forms, such as a servo motor, an actuator, etc., which can provide the driving force required for the swing engine 6 to rotate.

[0043] like Figure 1 , Figure 2 , Figure 3As shown, in this specific embodiment, the front center frame 12 and the rear center frame 22 are coaxially sleeved and assembled along the longitudinal center axis of the two. The front mounting bracket 1 and the rear mounting bracket 2 are assembled and look like an "I" shape from the side. The "cross" center line of the four mounting slots located by the front mounting plate 11 and the "cross" center line of the four mounting slots located by the rear mounting plate 21 are mirror images of each other along the cross section perpendicular to the longitudinal center axis of the propulsion and attitude and orbit control integrated power system. The thrust center lines of the fixed engine 3 and the swing engine 4 installed in the corresponding mounting slots are coplanar. The center of mass position of the aircraft is located between the front mounting plate 11 and the rear mounting plate 21 in the longitudinal direction, and changes in the longitudinal direction as the front center frame 12 and the rear center frame 22 slide relative to each other.

[0044] In order to reduce the structural mass, in this specific embodiment, the front mounting plate 11, the front center frame 12, the rear mounting plate 21, and the rear center frame 22 all adopt a hollow structure.

[0045] like Figure 1 , Figure 2 , Figure 3 , Fig.12 , Fig.13 As shown, in this specific embodiment, a guide rail is also provided between the front center frame 12 and the rear center frame 22, and the guide rail can be controlled to slide along the guide rail to change the distance between the front mounting plate 11 and the rear mounting plate 21, and at the same time, the longitudinal position of the center of mass of the aircraft is also synchronously adjusted.

[0046] It should be noted that the front center frame 12 and the rear center frame 22 are not limited to columnar structures with square cross-sections, but can also be columnar structures with circular cross-sections or other shapes. A guide rail, a slider or a pulley can be set between the front center frame 12 and the rear center frame 22, as long as a sliding pair capable of producing controlled relative movement is formed. The front center frame 12 and the rear center frame 22 can also be combined into one in the form of a fixed set. In this case, there can be no relative sliding between the front center frame 12 and the rear center frame 22, and the position of the center of mass of the aircraft cannot be actively changed. However, the position of the line of action of the resultant force can be moved by adjusting the thrust of the fixed engine 3 and the swing engine 4 to adapt to the change of the center of mass of the aircraft. Correspondingly, the supporting systems such as limit, detection, and servo control can be implemented by those skilled in the art in combination with common knowledge and will not be described in detail.

[0047] like Figure 1 , Figure 4 , Figure 5 , Fig.12 , Fig.13As shown, in this specific embodiment, the propellant supply system 5 is composed of a propellant tank 51 and a high-pressure gas cylinder 52. The propellant tank 51 and the high-pressure gas cylinder 52 are installed on the outer wall of the front center frame 12. The high-pressure gas cylinder 52 is connected to the propellant tank 51 through a pipeline, a one-way valve, and an electromagnetic valve. The propellant tank 51 is connected to the propellant injection ports of the fixed engine 3 and the swing engine 4 through the pipeline, the electromagnetic valve, and the one-way valve. The high-pressure gas cylinder 52 contains high-pressure helium, and the propellant tank 51 contains propellant. When the electromagnetic valve on the pipeline is opened, the high-pressure helium in the high-pressure gas cylinder 52 enters the propellant tank 51, and the propellant is pressurized and pushed to the propellant injection ports of the fixed engine 3 and the swing engine 4.

[0048] The fixed engine 3 and the swing engine 4 are rocket engines / gas generators using liquid fuel or colloidal fuel. The propellant can be a single component or a double component. If it is a double component propellant, different propellants are stored in multiple different propellant tanks 51 respectively.

[0049] The swing engine 4 has two working states, an initial propulsion state and an attitude and orbit control state. In the initial propulsion state, as a propulsion engine, the swing engine 4 is placed in a longitudinal limit position so that the nozzle points perpendicular to the disk surface of the rear mounting disk (21) and is locked by the detonating cord 7. In this state, the swing engine 4 is used for the propulsion of the aircraft. Since the thrust directions of the four swing engines 4 are all deviated from the center of mass, by changing the thrust size or working time, the attitude control can be achieved while propulsion. In the attitude and orbit control state, the swing engine 4 is placed in a radial limit lock so that the nozzle points parallel to the disk surface of the rear mounting disk 21. In this state, the swing engine 4 is no longer used for the propulsion of the aircraft, but is used as an attitude and orbit control engine. Due to the state conversion of the swing engine 4, the consumption of propellant, the consumption of high-pressure helium, etc., the overall center of mass of the aircraft will also change. At this time, the propulsion and attitude and orbit control integrated power system can adaptively adjust the center of mass position so that the line of action of the combined force of the orbit control always follows the center of mass. There are two specific ways.

[0050] like Figure 1 , Figure 4 , Figure 5 , Figure 7 , Figure 8 As shown, the swing engine 4 of this specific embodiment is in the initial propulsion state, the swing engine 4 is rotated to be placed in a limited position where the nozzle is perpendicular to the rear mounting plate 21 and the plate surface is rearward, and is locked by the detonating cord 7, and the swing engine 4 is ignited for the propulsion of the aircraft. By adjusting the thrust size or working time of the four fixed engines 3 and the four swing engines 4, a torque is formed relative to the center of mass of the aircraft, and the aircraft attitude control is performed while propulsion.

[0051] like Fig. 9 , Fig.10 , Fig.11 , Fig.12 , Fig.13 As shown, this is the first way of using the swing engine 4 in the attitude and orbit control state of this specific embodiment. The detonating cord 7 is detonated to release the position lock of the swing engine 4. Under the action of the tension of the spring 6, the swing engine 4 rotates around the rotation axis in the longitudinal symmetric plane of the installation groove until the nozzle is directed parallel to the radial limit position of the rear installation plate 21. The front center frame 12 and the rear center frame 22 slide relatively and controllably, actively changing the longitudinal position of the center of mass of the aircraft, so that the longitudinal distance from the center of mass of the aircraft to the fixed engine 3 and the swing engine 4 is inversely proportional to the thrust generated by the fixed engine 3 and the swing engine 4 with the same nozzle direction on the front installation plate 11 and the rear installation plate 21. According to the principle of force synthesis, the line of action of the orbit control force on the aircraft passes through the center of mass and is perpendicular to the longitudinal center axis of the aircraft. The resultant force is the sum of the thrust forces generated by the two engines. The fixed engine 3 and the swing engine 4 are ignited separately or simultaneously to generate thrusts of different magnitudes / directions, which generate torque relative to the center of mass to achieve the attitude control of the aircraft.

[0052] like Fig. 9 , Fig.10 , Fig.11 , Fig.12 , Fig.13 As shown, this is the second way of using the swing engine 4 in the attitude and orbit control state of this specific embodiment. The detonating cord 7 is detonated to release the position lock of the swing engine 4. Under the action of the tension of the spring 6, the swing engine 4 rotates around the rotation axis in the longitudinal symmetric plane of the installation groove until the nozzle points to the radial limit lock parallel to the disk surface of the rear installation disk 21, and does not actively change the longitudinal position of the center of mass of the aircraft. The fixed engine 3 and the swing engine 4 on the front installation disk 11 and the rear installation disk 21 point to the same nozzle. The engine is ignited and works at the same time, and the thrust generated by the two engines is inversely proportional to the longitudinal distance from the center of mass of the aircraft. According to the principle of force synthesis, the line of action of the orbit control force on the aircraft passes through the center of mass and is perpendicular to the longitudinal center axis of the aircraft. The resultant force is the sum of the thrust forces generated by the two engines, and the aircraft orbit control action is realized. The fixed engine 3 and the swing engine 4 are ignited separately or simultaneously to generate thrusts of different magnitudes / directions, which generate torque relative to the center of mass to realize the attitude control of the aircraft.

[0053] In special circumstances, when the longitudinal distances from the center of mass of the aircraft to the fixed engine 3 and the swing engine 4 are equal, and the thrusts of the fixed engine 3 and the swing engine 4 whose engine nozzles on the front mounting plate 11 and the rear mounting plate 21 point to the same direction are also equal, the line of action of the combined thrusts of the aforementioned fixed engine 3 and the swing engine 4 passes through the center of mass of the aircraft and is perpendicular to the longitudinal center axis of the aircraft, thereby realizing the orbital control action of the aircraft and generating twice the overload when a single fixed engine 3 or swing engine 4 is working.

[0054] The user can select which of the two methods to use when the swing engine 4 is in the attitude and orbit control state according to the convenience of his own design, or the two methods can be used in combination.

[0055] The maximum thrust generated by the fixed engine 3 and the swing engine 4 can be the same or different. The functions of the spring 6 and the detonating cord 7 can also be realized in other forms, such as the spring 6 can be replaced by other force storage devices such as a torsion spring, and the detonating cord 7 can be replaced by other controllable unlocking locking devices such as an explosive bolt.

[0056] The beneficial technical effects achieved by the present invention are:

[0057] The swing engine with changeable thrust direction is used to perform propulsion and attitude and orbit control functions in a time-sharing manner, avoiding the addition of an independent propulsion stage system to the aircraft, and effectively reducing the structural mass and system design complexity caused by the addition of new tanks, pressurization systems, pipelines, etc. The longitudinal position of the center of mass of the aircraft is changed by the relative controlled sliding of the front center frame and the rear center frame, so that the installation position of the orbit control engine is no longer constrained by the longitudinal center of mass position of the aircraft, and the traditional introduction of dead weight such as increasing the balancing mass to make the thrust center line of the orbit control engine pass through the center of mass of the aircraft is also avoided. By moving or adjusting the thrust of the fixed engine and the swing engine in the same direction by the front and rear mounting brackets, the principle of force synthesis is used to make the resultant force equal to the sum of the thrusts of the fixed engine and the swing engine, and the line of action of the resultant force always coincides with the center of mass of the aircraft, avoiding the interference of the torque formed by the engine thrust relative to the center of mass on the flight control during the orbit control action, which can effectively improve the control accuracy. By synthesizing the thrust of fixed engines and swinging engines in the same direction, we can further expand the thrust synthesis of more engines in the same direction, instead of the traditional method of developing new and larger orbit control engines. We can use one type of orbit control engine to meet greater orbit control thrust requirements, thus avoiding the funding, cycle and technical maturity issues brought about by developing new and larger thrust orbit control engines.

[0058] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. An adaptive mass center propulsion and attitude and orbit control integrated power system, characterized by: It comprises a front mounting bracket (1), a rear mounting bracket (2), a fixed engine (3), a swing engine (4), and a propellant supply system (5); the propulsion and attitude and orbit control integrated power system is installed at the rear of the aircraft, and its longitudinal center axis coincides with the longitudinal center axis of the aircraft, and the front mounting bracket (1) is located on one side of the forward direction of the aircraft; The front mounting bracket (1) comprises a front mounting plate (11) and a front center frame (12); the longitudinal center axis of the front center frame (12) coincides with the normal center axis of the front mounting plate (11); the front mounting plate (11) is provided with four mounting grooves symmetrically distributed in a "cross" shape along the normal direction of the plate surface; a fixed engine (3) is installed in each mounting groove; the nozzle of the fixed engine (3) points to the edge of the front mounting plate (11); The rear mounting bracket (2) comprises a rear mounting plate (21) and a rear center frame (22); the longitudinal center axis of the rear center frame (22) coincides with the normal center axis of the rear mounting plate (21); the rear mounting plate (21) is provided with four mounting slots symmetrically distributed in a "cross" shape along the normal direction of the plate surface; a swing engine (4) is mounted in each mounting slot in an articulated manner; the swing engine (4) can rotate around a hinge axis in a longitudinal symmetric plane of the mounting slot under the drive of a drive device; a limit locking structure is provided in the radial and longitudinal directions of the mounting slot; the swing engine (4) is initially rotated to a longitudinal limit position in which the nozzle is directed perpendicular to the rear surface of the rear mounting plate (21); the swing engine (4) is locked by a locking device that can be unlocked; after the swing engine (4) is unlocked, it turns under the drive of the drive device and rotates around the hinge axis in the longitudinal symmetric plane of the mounting slot to a radial limit position in which the nozzle is directed parallel to the rear mounting plate (21) surface; The cross center lines of the four installation slots located on the front installation plate (11) and the cross center lines of the four installation slots located on the rear installation plate (21) are mirror images of each other along a cross section perpendicular to the longitudinal center axis of the propulsion and attitude and orbit control integrated power system, and the thrust center lines of the fixed engine (3) and the swing engine (4) installed in the corresponding installation slots are coplanar; The propellant supply system (5) is installed on the front center frame, and the propellant supply system is connected with the propellant injection ports of the fixed engine and the swing engine through pipelines, solenoid valves, and one-way valves.

2. The propulsion and attitude and orbit control integrated power system according to claim 1 is characterized in that: The propellant supply system (5) comprises a propellant tank (51) and a high-pressure gas cylinder (52). The propellant tank (51) and the high-pressure gas cylinder (52) are mounted on the outer wall of the front center frame (12). The high-pressure gas cylinder (52) and the propellant tank (51) are connected via a pipeline, a one-way valve, and an electromagnetic valve. The propellant tank (51) is connected to the propellant injection ports of the fixed engine (3) and the swing engine (4) via the pipeline, the electromagnetic valve, and the one-way valve. The high-pressure gas cylinder (52) contains high-pressure helium, and the propellant tank (51) contains propellant. When the electromagnetic valve on the pipeline is opened, the high-pressure helium in the high-pressure gas cylinder (52) enters the propellant tank (51), pressurizing the propellant and pushing it to the propellant injection ports of the fixed engine (3) and the swing engine (4).

3. The propulsion and attitude and orbit control integrated power system according to claim 1 is characterized in that: The propulsion and attitude and orbit control integrated power system further comprises a spring (6) and a detonating cord (7), wherein the detonating cord (7) serves as a controllable unlocking locking device, the swing engine (4) is rotated to be placed in a longitudinal limit position where the nozzle is perpendicular to the rear mounting plate (21) and faces backward, the detonating cord (7) is wound along the circumferential direction of the rear mounting plate (21) to constrain and lock the four swing engines (4), and the spring (6) serves as a driving device, one end of which is hung on the tail of the swing engine (4), and the other end of which is radially stretched along the rear mounting plate (21) and hung on the bottom of its mounting groove, thereby forming a driving force for rotating the swing engine (6) around the hinge axis within the longitudinal symmetry plane of the mounting groove.

4. The propulsion and attitude and orbit control integrated power system according to claim 1 is characterized in that: The swing engine (4) has a rotating shaft symmetrically arranged along the radial outer wall of the combustion chamber, a pair of bearings are symmetrically arranged in the wall surface of the installation groove and in the longitudinal symmetry plane of the installation groove, and the swing engine (4) is rotatably connected to the installation groove of the rear installation plate (21) through the rotating shaft and the bearings.

5. The propulsion and attitude and orbit control integrated power system according to claim 1 is characterized in that: The swing engine (4) is rotated so that the nozzle is perpendicular to the rear mounting plate (21) and locked in a rearward limit position. The swing engine (4) is ignited to propel the aircraft. By adjusting the thrust size or working time of the four fixed engines (3) and the four swing engines (4), a torque is formed relative to the center of mass of the aircraft, and the attitude of the aircraft is controlled while propulsion is performed.

6. The propulsion and attitude and orbit control integrated power system according to claim 1 is characterized in that: The fixed engine (3) and the swing engine (4) are rocket engines / gas generators that use liquid fuel or colloid fuel.

7. The propulsion and attitude and orbit control integrated power system according to claim 1 is characterized in that: The propellants used by the fixed engine (3) and the swing engine (4) are monopropellants or bipropellants.

8. The propulsion and attitude and orbit control integrated power system according to claim 1 is characterized in that: After the swing engine (4) is unlocked, it turns under the drive of the driving device and rotates around the hinge axis in the longitudinal symmetric plane of the installation groove until the nozzle points to the radial limit position parallel to the disk surface of the rear installation disk (21) and is locked without actively changing the longitudinal position of the center of mass of the aircraft. The fixed engine (3) and the swing engine (4) whose nozzles on the front installation disk (11) and the rear installation disk (21) point to the same direction are ignited and operated at the same time. The thrust of the fixed engine (3) and the swing engine (4) is adjusted so that the thrust generated by the two engines is inversely proportional to the longitudinal distance from the center of mass of the aircraft. According to the principle of force synthesis, the line of action of the resultant force of the thrust generated by the fixed engine (3) and the swing engine (4) passes through the center of mass of the aircraft and is perpendicular to the longitudinal center axis of the aircraft. The resultant force is equal to the sum of the thrusts generated by the fixed engine (3) and the swing engine (4), thereby realizing the orbit control action of the aircraft. The fixed engine (3) and the swing engine (4) are ignited separately or simultaneously to generate thrusts of different magnitudes / directions, generating torque relative to the center of mass, thereby realizing the attitude control of the aircraft.

9. The propulsion and attitude and orbit control integrated power system according to claim 1 is characterized in that: The front center frame (12) and the rear center frame (22) form a sliding pair capable of producing controlled relative movement. The center of mass of the aircraft is longitudinally located between the front mounting plate (11) and the rear mounting plate (21), and changes longitudinally as the front center frame (12) and the rear center frame (22) slide relative to each other.

10. The propulsion and attitude and orbit control integrated power system according to claim 9 is characterized in that: The front center frame (12) is a columnar structure with a square cross section, and the rear center frame (22) is a columnar structure with a square cross section. The front center frame (12) and the rear center frame (22) are coaxially sleeved and assembled along their longitudinal center axes.

11. The propulsion and attitude and orbit control integrated power system according to claim 9 is characterized in that: A guide rail is also provided between the front center frame (12) and the rear center frame (22), and the front center frame (12) slides relatively to the rear center frame (22) along the guide rail in a controlled manner.

12. The propulsion and attitude and orbit control integrated power system according to any one of claims 9 to 11, characterized in that: After the swing engine (4) is unlocked, it turns under the drive of the driving device and rotates around the hinge axis in the longitudinal symmetric plane of the installation groove until the nozzle points to the radial limit position parallel to the disk surface of the rear installation disk (21) and is locked. The longitudinal position of the center of mass of the aircraft is actively changed by the front central frame (12) and the rear central frame (22) sliding relatively in a controlled manner, so that the distance between the center of mass of the aircraft and the front installation disk (11) and the rear installation disk (21) is inversely proportional to the thrust generated by the fixed engine (3) and the swing engine (4) on the front installation disk (11) and the rear installation disk (21) with the same nozzle direction. The corresponding engine is ignited to generate thrust. According to the principle of force synthesis, the line of action of the resultant force on the aircraft passes through the center of mass of the aircraft and is perpendicular to the longitudinal center axis of the aircraft. The resultant force is equal to the sum of the thrusts generated by the fixed engine (3) and the swing engine (4), thereby realizing the orbit control action of the aircraft. The fixed engine (3) and the swing engine (4) are ignited separately or simultaneously to generate thrusts of different magnitudes / directions, which generate torque relative to the center of mass, thereby realizing the attitude control of the aircraft.

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