A model device for force measurement test of attitude and orbit control coupled jet interference

Abstract

This invention provides a model device for force measurement tests of attitude and orbit control coupled jet interference, comprising a head, an orbit control nozzle section, an orbit control air path, an attitude control nozzle section, an attitude control air path, a force balance, and a support rod. The first end of the orbit control nozzle section is connected to the head, and an orbit control pressure stabilizing chamber is located inside the orbit control nozzle section. The first end of the attitude control nozzle section is connected to the second end of the orbit control nozzle section, and an attitude control pressure stabilizing chamber is located inside the attitude control nozzle section. The first end of the force balance is connected to the second end of the attitude control nozzle section, and the first end of the support rod is connected to the second end of the force balance. The first end of the orbit control air path is connected to the orbit control pressure stabilizing chamber, and the first end of the attitude control air path is also connected to the attitude control pressure stabilizing chamber. This invention enables force measurement tests of jet interference under simulated jet pressure and different simulated flight altitude conditions at scaled-down scale, and allows for direct measurement of the aerodynamic characteristics of attitude and orbit control coupled jet interference in aircraft.

Description

Technical Field

[0001] This invention relates to the field of jet interference force measurement technology, and in particular to a model device for attitude and orbit control coupled jet interference force measurement test. Background Technology

[0002] The reaction force (RCS) generated by the lateral jet can alter the attitude or trajectory of an aircraft, compensating for insufficient aerodynamic control surface efficiency and rapidly changing flight status. It has been applied to various aircraft both domestically and internationally, such as the PAC-3, THAAD, Aster, HTV-2, return vehicles, and several new high-maneuverability aircraft in my country. RCS control technology has become an essential key technology for these aircraft. However, the jet and external flow interference significantly alter the surface and spatial flow of the aircraft, generating additional aerodynamic forces and moments. Control system design requires accurate surface load characteristics and aerodynamic properties, and wind tunnel testing and numerical prediction are crucial means of obtaining these results. Wind tunnel testing is also an important way to verify the accuracy of numerical simulation methods and guide their improvement.

[0003] The lateral jets from the orbit control system generate additional disturbance moments that cause the aircraft to pitch up or down. To ensure normal flight, the aerodynamic control surfaces are adjusted to balance these disturbance moments. Under certain conditions, if the aerodynamic control surfaces fail, the attitude control nozzle jets are used to generate control moments that balance the additional disturbance moments from the orbit control jets, thus enabling normal flight. Unlike conventional standalone orbit control or attitude control force measurement test models, the attitude-orbit-control coupled jet disturbance force measurement test model requires consideration of the arrangement of the orbit control and attitude control air paths within the scaled-down model, as well as the design of the pressure stabilization chambers for each nozzle under scaled-down conditions, resulting in a more complex structure.

[0004] Currently, there is no experimental model device for force measurement of attitude and orbit control coupled jet interference. Therefore, we look forward to developing a model for force measurement of attitude and orbit control jet interference to meet the above research needs and obtain the change law of aerodynamic characteristics of the aircraft under attitude and orbit control coupled jet conditions. Summary of the Invention

[0005] The purpose of this invention is to provide a model device for force measurement tests of attitude and orbit control coupled jet interference, which can realize jet interference force measurement tests under scaled conditions with different jet pressures and different simulated flight altitudes, and can directly measure the aerodynamic characteristics of attitude and orbit control coupled jet interference of aircraft.

[0006] This invention provides a model device for force measurement tests of attitude and orbit control coupled jet interference, comprising:

[0007] head;

[0008] The track control nozzle section has its first end connected to the head, and the interior of the track control nozzle section is provided with a track control pressure stabilizing chamber. A track control nozzle is provided on the side wall of the track control nozzle section, and the track control nozzle is connected to the track control pressure stabilizing chamber.

[0009] The attitude control nozzle section has a first end connected to the second end of the track control nozzle section. The attitude control nozzle section has an attitude control pressure stabilizing chamber inside and an attitude control nozzle on its side wall. The attitude control nozzle is connected to the attitude control pressure stabilizing chamber.

[0010] A force balance, the first end of which is connected to the second end of the attitude control nozzle section, and the force balance has a first mounting through hole inside, which passes through both ends of the force balance;

[0011] A support rod, the first end of which is connected to the second end of the force balance, and the second end of which is used to connect to wind tunnel equipment; the support rod has a second mounting through hole inside, which passes through both ends of the support rod;

[0012] The track control air circuit has a first end that passes through the second mounting through hole, the first mounting through hole and the attitude control nozzle section in sequence, and the first end of the track control air circuit is connected to the track control pressure stabilizing chamber. The second end of the track control air circuit is used to connect to the first high-pressure air source.

[0013] The attitude control air path has a first end that passes through the second mounting through hole and the first mounting through hole in sequence, and the first end of the attitude control air path is connected to the attitude control pressure stabilizing chamber. The second end of the attitude control air path is used to connect to the second high-pressure air source.

[0014] According to the present invention, a model device for force measurement test of attitude and track control coupled jet interference is provided, wherein the head is a conical structure, and a first mounting cavity is provided at one end of the head facing the track control nozzle section; the inner sidewall of the first mounting cavity is provided with a first internal thread, and the outer sidewall of the first end of the track control nozzle section is provided with a first external thread adapted to the first internal thread; the first end of the track control nozzle section is disposed in the first mounting cavity, and the first end of the track control nozzle section is threadedly connected to the inner sidewall of the first mounting cavity.

[0015] According to the present invention, a model device for force measurement test of attitude and track control coupled jet interference is provided, wherein the outer diameter of the head gradually increases from the first end to the second end, and the outer diameter of the second end of the head is equal to the outer diameter of the track control nozzle section.

[0016] According to the present invention, a model device for force measurement test of attitude and track control coupled jet interference is provided, wherein a first vent is provided at the first end of the track control nozzle section, and the first vent is connected to the track control pressure stabilizing chamber;

[0017] A first sealing assembly for sealing the first vent hole is provided at the first end of the track control nozzle section. The first sealing assembly includes a first connecting plug and a first sealing gasket. A first mounting interface is provided on the end face of the first end of the track control nozzle section. The first mounting interface is connected to the first vent hole. The first connecting plug is threadedly connected to the first mounting interface. The first sealing gasket is disposed between the first connecting plug and the first vent hole.

[0018] According to the present invention, a model device for force measurement test of attitude control coupled jet interference is provided, wherein the outer side wall of the second end of the track control nozzle section is provided with an installation step, the first end of the attitude control nozzle section is fitted onto the installation step, and the second end of the track control nozzle section is connected and fixed to the first end of the attitude control nozzle section by a first pin.

[0019] According to the present invention, a model device for force measurement test of attitude and track control coupled jet interference is provided, wherein a second mounting interface is provided on the end face of the second end of the track control nozzle section, and the second mounting interface is connected to the track control pressure stabilizing chamber; the first end of the track control air circuit is threadedly connected to the second mounting interface, and a first sealing ring is provided between the track control air circuit and the second mounting interface.

[0020] According to the present invention, a model device for force measurement test of attitude control coupled jet interference is provided, wherein a second vent is provided at the inner end of the attitude control nozzle section, and the second vent is connected to the attitude control pressure stabilizing chamber.

[0021] A second sealing assembly for sealing the second vent hole is provided on the attitude control nozzle section. The second sealing assembly includes a second connecting plug and a second sealing gasket. A third mounting interface is provided at the inner end of the attitude control nozzle section. The third mounting interface is connected to the second vent hole. The second connecting plug is threadedly connected to the third mounting interface. The second sealing gasket is disposed between the second connecting plug and the second vent hole.

[0022] According to the present invention, a model device for force measurement test of attitude control coupled jet interference is provided, wherein the end face of the second end of the attitude control nozzle section is provided with a second mounting cavity, the first end of the force balance is installed in the second mounting cavity, and the first end of the force balance and the second end of the attitude control nozzle section are connected and fixed by a second pin.

[0023] According to the present invention, a model device for force measurement test of attitude control coupled jet interference is provided, wherein a mounting boss is provided between the attitude control pressure stabilizing chamber and the second mounting cavity, and a fourth mounting interface is provided on the mounting boss, the fourth mounting interface being connected to the attitude control pressure stabilizing chamber; the first end of the attitude control air circuit is threadedly connected to the fourth mounting interface, and a second sealing ring is provided between the attitude control air circuit and the fourth mounting interface.

[0024] According to the present invention, a model device for force measurement test of attitude and orbit control coupled jet interference is provided, wherein the first end of the support rod is provided with a conical hole, and the second end of the force measuring balance is sealed and installed in the conical hole.

[0025] The present invention provides a model device for force measurement tests of attitude and orbit control coupled jet interference, comprising a head, an orbit control nozzle section, an orbit control air path, an attitude control nozzle section, an attitude control air path, a force balance, and a support rod. The first end of the orbit control nozzle section is connected to the head. An orbit control pressure stabilizing chamber is set inside the orbit control nozzle section, and an orbit control nozzle is set on the side wall of the orbit control nozzle section, connecting the orbit control nozzle to the orbit control pressure stabilizing chamber. The first end of the attitude control nozzle section is connected to the second end of the orbit control nozzle section. An attitude control pressure stabilizing chamber is set inside the attitude control nozzle section, and an attitude control nozzle is set on the side wall of the attitude control nozzle section, connecting the attitude control nozzle to the attitude control pressure stabilizing chamber. The first end of the force balance is connected to the second end of the attitude control nozzle section, and a second support rod is set inside the force balance. A first mounting through-hole is provided, allowing it to pass through both ends of the force balance. The first end of a support rod is connected to the second end of the force balance, and the second end of the support rod is used to connect to wind tunnel equipment. A second mounting through-hole is provided inside the support rod, allowing it to pass through both ends of the support rod. The first end of the rail control air path sequentially passes through the second mounting through-hole, the first mounting through-hole, and the attitude control nozzle section, and is connected to the rail control pressure stabilizing chamber. The second end of the rail control air path is used to connect to the first high-pressure air source. The first end of the attitude control air path sequentially passes through the second mounting through-hole and the first mounting through-hole, and is connected to the attitude control pressure stabilizing chamber. The second end of the attitude control air path is used to connect to the second high-pressure air source. Therefore, the model device provided by this invention for force measurement tests of attitude-rail-control coupled jet interference, by setting the rail control air path and attitude control air path to separate air supply, can realize jet interference force measurement tests under scaled conditions simulating different jet pressures and different simulated flight altitudes. By setting the model device provided by this invention for force measurement test of attitude and orbit control coupled jet interference in a wind tunnel, the aerodynamic characteristics of attitude and orbit control coupled jet interference of an aircraft can be directly measured, providing accurate aerodynamic characteristics for the design of aircraft attitude and orbit control. Attached Figure Description

[0026] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0027] Figure 1 This is a schematic diagram of the model device for force measurement test of attitude and orbit control coupled jet interference according to the present invention.

[0028] Explanation of reference numerals in the attached figures:

[0029] 1. Head; 101. First mounting cavity; 2. Track control nozzle section; 201. Track control pressure stabilizing chamber; 202. Track control nozzle; 203. First vent hole; 3. Attitude control nozzle section; 301. Attitude control pressure stabilizing chamber; 302. Attitude control nozzle; 4. Track control air path; 5. Attitude control air path; 6. Force balance; 601. First mounting through hole; 7. Support rod; 701. Second mounting through hole; 8. First connecting plug; 9. First sealing gasket; 10. First pin; 11. First sealing ring; 12. Second connecting plug; 13. Second sealing gasket; 14. Second pin; 15. Second sealing ring. Detailed Implementation

[0030] The technical solution of the present invention will be clearly and completely described below with reference to the embodiments. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0031] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting this invention.

[0032] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the stated features. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified. Furthermore, the terms "installed," "connected," and "linked" should be interpreted broadly; for example, they may refer to a fixed connection, a detachable connection, or an integral connection; they may refer to a mechanical connection or an electrical connection; they may refer to a direct connection or an indirect connection through an intermediate medium; and they may refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0033] like Figure 1 As shown, the model device for force measurement test of attitude and orbit control coupled jet interference according to an embodiment of the present invention includes a head 1, an orbit control nozzle section 2, an attitude control nozzle section 3, an orbit control air path 4, an attitude control air path 5, a force measuring balance 6, and a support rod 7. The first end of the orbit control nozzle section 2 is connected to the head 1.

[0034] The track control nozzle section 2 has a track control pressure stabilizing chamber 201 inside. A track control nozzle 202 is located on the side wall of the track control nozzle section 2. One end of the track control nozzle 202 is connected to the track control pressure stabilizing chamber 201, and the other end is connected to the outside. The attitude control nozzle section 3 has its first end connected to the second end of the track control nozzle section 2. The attitude control nozzle section 3 has an attitude control pressure stabilizing chamber 301 inside. An attitude control nozzle 302 is located on the side wall of the attitude control nozzle section 3. One end of the attitude control nozzle 302 is connected to the attitude control pressure stabilizing chamber 301, and the other end is connected to the outside. The force balance 6 has its first end connected to the second end of the attitude control nozzle section 3. The force balance 6 has a first mounting through hole 601 inside, through which the force balance...

[0035] The force balance 6 has two ends. The first end of the support rod 7 is connected to the second end of the force balance 6, and the second end of the support rod 7 is used to connect to the wind tunnel equipment. The support rod 7 has a second mounting through hole 701 inside, which passes through both ends of the support rod 7. The first end of the rail control air circuit 4 passes through the second mounting through hole in sequence.

[0036] The attitude control air passage 4 includes a hole 701, a first mounting through hole 601, and an attitude control nozzle section 3. The first end of the attitude control air passage 4 is connected to the pressure stabilizing chamber 201 of the attitude control 5, and the second end of the attitude control air passage 4 is connected to the first high-pressure air source. The first end of the attitude control air passage 5 passes through the second mounting through hole 701 and the first mounting through hole 601 in sequence, and the first end of the attitude control air passage 5 is connected to the attitude control pressure stabilizing chamber 301. The second end of the attitude control air passage 5 is connected to the second high-pressure air source.

[0037] Therefore, the model device for attitude and orbit control coupled jet interference force measurement test according to the embodiment of the present invention, by separately connecting the orbit control air path 4 to the orbit control pressure stabilizing chamber 201 and separately connecting the attitude control air path 5 to the attitude control pressure stabilizing chamber 301, thereby setting the orbit control air path 4 and attitude control air path 5 to be supplied with air independently, can realize jet interference force measurement test under scaled conditions simulating different jet pressures and different simulated flight altitudes. This embodiment of the present invention is used for attitude and orbit control coupled jet interference force measurement test.

[0038] The model device is set up in a wind tunnel, which can directly measure the aerodynamic characteristics of the aircraft's attitude and orbit control coupled jet interference, providing accurate aerodynamic characteristics for the design of aircraft attitude and orbit control.

[0039] In some embodiments of the present invention, the head 1 has a conical structure, and a first mounting cavity 101 is provided at one end of the head 1 facing the track control nozzle section 2. The inner sidewall of the first mounting cavity 101 is provided with a first internal thread, and the outer sidewall of the first end of the track control nozzle section 2 is provided with a first external thread adapted to the first internal thread. The first end of the track control nozzle section 2 is disposed in the first mounting cavity 101, and the first end of the track control nozzle section 2 is threadedly connected to the inner sidewall of the first mounting cavity 101, thereby realizing a reliable connection between the head 1 and the track control nozzle section 2.

[0040] Specifically, the outer diameter of the head 1 gradually increases from the first end to the second end, and the outer diameter of the second end of the head 1 is equal to the outer diameter of the track control nozzle section 2, so as to make a smooth transition connection between the head 1 and the track control nozzle section 2.

[0041] In some embodiments of the present invention, a first vent 203 is provided at the first end of the track control nozzle section 2, and the first vent 203 is connected to the track control pressure stabilizing chamber 201. A first sealing assembly for sealing the first vent 203 is provided at the first end of the track control nozzle section 2, wherein the first sealing assembly includes a first connecting plug 8 and a first sealing gasket 9. A first mounting interface is provided on the end face of the first end of the track control nozzle section 2, and the first mounting interface is connected to the first vent 203. The first connecting plug 8 is threadedly connected to the first mounting interface, and the first sealing gasket 9 is disposed between the first connecting plug 8 and the first vent 203, thereby achieving the sealing and sealing of the first vent 203, and thus ensuring the airtightness of the track control pressure stabilizing chamber 201.

[0042] In some embodiments of the present invention, the outer side wall of the second end of the track control nozzle section 2 is provided with an installation step, the first end of the attitude control nozzle section 3 is fitted onto the installation step, and the second end of the track control nozzle section 2 and the first end of the attitude control nozzle section 3 are connected and fixed by a first pin 10, thereby realizing a reliable connection between the track control nozzle section 2 and the attitude control nozzle section 3.

[0043] In some embodiments of the present invention, a second mounting interface is provided on the end face of the second end of the track control nozzle section 2, and the second mounting interface is connected to the track control pressure stabilizing chamber 201. The first end of the track control air passage 4 is threadedly connected to the second mounting interface, and a first sealing ring 11 is provided between the track control air passage 4 and the second mounting interface, thereby achieving a sealed connection between the track control air passage 4 and the track control pressure stabilizing chamber 201.

[0044] In some embodiments of the present invention, a second vent is provided at the inner end of the attitude control nozzle section 3, and the second vent is connected to the attitude control pressure stabilizing chamber 301. A second sealing assembly for sealing the second vent is provided on the attitude control nozzle section 3, wherein the second sealing assembly includes a second connecting plug 12 and a second sealing gasket 13. A third mounting interface is provided at the inner end of the attitude control nozzle section 3, and the third mounting interface is connected to the second vent. The second connecting plug 12 is threadedly connected to the third mounting interface, and the second sealing gasket 13 is disposed between the second connecting plug 12 and the second vent, thereby achieving a seal for the second vent and ensuring the airtightness of the attitude control pressure stabilizing chamber 301.

[0045] In some embodiments of the present invention, the end face of the second end of the attitude control nozzle section 3 is provided with a second mounting cavity, the first end of the force balance 6 is installed in the second mounting cavity, and the first end of the force balance 6 and the second end of the attitude control nozzle section 3 are connected and fixed by a second pin 14, thereby realizing a reliable connection between the attitude control nozzle section 3 and the force balance 6.

[0046] In some embodiments of the present invention, a mounting boss is provided between the attitude control pressure stabilizing chamber 301 and the second mounting cavity, and a fourth mounting interface is provided on the mounting boss, which is connected to the attitude control pressure stabilizing chamber 301. The first end of the attitude control air passage 5 is threadedly connected to the fourth mounting interface, and a second sealing ring 15 is provided between the attitude control air passage 5 and the fourth mounting interface, thereby achieving a sealed connection between the attitude control air passage 5 and the attitude control pressure stabilizing chamber 301.

[0047] In some embodiments of the present invention, the first end of the support rod 7 is provided with a conical hole, and the second end of the force balance 6 is sealed and installed in the conical hole, thereby realizing a reliable connection between the support rod 7 and the force balance 6.

[0048] In some embodiments of the present invention, the inner diameter of the track control pressure stabilizing chamber 201 is more than twice the throat diameter of the track control nozzle section 2.

[0049] In some embodiments of the present invention, the outer diameter of the track control nozzle section 2 is equal to the outer diameter of the first end of the attitude control nozzle section 3.

[0050] In some embodiments of the present invention, two pin holes may be provided at the second end of the track control nozzle section 2. The two pin holes are located on opposite sides of the track control nozzle 2, and the two pin holes are located on the same cross section and their axes form a 90-degree angle. The two pin holes are on the same axis as the two pin holes on the first end sidewall of the attitude control nozzle section 3.

[0051] In some embodiments of the present invention, the internal diameter of the track control air passage 4 is not less than twice the throat diameter of the track control nozzle section 2.

[0052] In some embodiments of the present invention, the inner diameter of the attitude control pressure stabilizing chamber 301 is more than twice the throat diameter of the attitude control nozzle section 3.

[0053] In some embodiments of the present invention, the internal diameter of the attitude control air passage 5 is not less than twice the throat diameter of the attitude control nozzle section 3.

[0054] In some embodiments of the present invention, the second end of the attitude control nozzle section 3 is provided with two pin holes. The two pin holes are located on opposite sides of the attitude control nozzle section 3, the two pin holes are located on the same cross section and the axes are at a 90-degree angle. The two pin holes are on the same axis as the two pin holes on the first end of the force balance 6.

[0055] In some embodiments of the present invention, a gap of not less than 2 mm is left between the attitude control air path 5 and the rail control air path 4, a gap of not less than 3 mm is left between the attitude control air path 5 and the inner wall of the force balance 6, and a gap of not less than 3 mm is left between the rail control air path 4 and the inner wall of the force balance 6.

[0056] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A model device for attitude-orbit control coupled jet interference force test, characterized in that, The utility model relates to a kind of test equipment for aerodynamic characteristics of spacecraft, including: Head; Orbit control nozzle section, the first end of the orbit control nozzle section is connected with the head, the inside of the orbit control nozzle section is equipped with orbit control plenum, and orbit control nozzle is equipped on the side wall of the orbit control nozzle section, and the orbit control nozzle is communicated with the orbit control plenum; Attitude control nozzle section, the first end of the attitude control nozzle section is connected with the second end of the orbit control nozzle section, the inside of the attitude control nozzle section is equipped with attitude control plenum, and attitude control nozzle is equipped on the side wall of the attitude control nozzle section, and the attitude control nozzle is communicated with the attitude control plenum; Force balance, the first end of the force balance is connected with the second end of the attitude control nozzle section, the inside of the force balance is equipped with first installation through-hole, and the first installation through-hole is through both ends of the force balance; Supporting rod, the first end of the supporting rod is connected with the second end of the force balance, and the second end of the supporting rod is used to be connected with wind tunnel equipment;The inside of the supporting rod is equipped with second installation through-hole, and the second installation through-hole is through both ends of the supporting rod; Orbit control gas path, the first end of the orbit control gas path is sequentially through the second installation through-hole, the first installation through-hole and the attitude control nozzle section, and the first end of the orbit control gas path is communicated with the orbit control plenum, and the second end of the orbit control gas path is used to be communicated with first high-pressure gas source; Attitude control gas path, the first end of the attitude control gas path is sequentially through the second installation through-hole and the first installation through-hole, and the first end of the attitude control gas path is communicated with the attitude control plenum, and the second end of the attitude control gas path is used to be communicated with second high-pressure gas source; The head is conical structure, and the end of the head towards the orbit control nozzle section is equipped with first installation cavity;The inner side wall of the first installation cavity is equipped with first internal thread, and the first end of the orbit control nozzle section outer side wall is equipped with the first external thread matched with the first internal thread, and the first end of the orbit control nozzle section is arranged in the first installation cavity, and the first end of the orbit control nozzle section is threadedly connected with the inner side wall of the first installation cavity; First air hole is equipped on the first end of the orbit control nozzle section, and the first air hole is communicated with the orbit control plenum;First plugging assembly for plugging the first air hole is equipped on the first end of the orbit control nozzle section, and the first plugging assembly includes first connecting plug and first sealing pad;First installation interface is equipped on the end face of the first end of the orbit control nozzle section, and the first installation interface is communicated with the first air hole, and the first connecting plug is threadedly connected with the first installation interface, and the first sealing pad is arranged between the first connecting plug and the first air hole; The second end outer side wall of the orbit control nozzle section is equipped with installation step, the first end of the attitude control nozzle section is sleeved on the installation step, and the second end of the orbit control nozzle section and the first end of the attitude control nozzle section are fixed by first pin connection;Second installation interface is equipped on the end face of the second end of the orbit control nozzle section, and the second installation interface is communicated with the orbit control plenum;The first end of the orbit control gas path is threadedly connected with the second installation interface, and first sealing ring is arranged between the orbit control gas path and the second installation interface; A second vent hole is arranged at the inner end of the attitude control nozzle section, and the second vent hole is communicated with the attitude control plenum; a second blocking assembly for blocking the second vent hole is arranged on the attitude control nozzle section, and the second blocking assembly comprises a second connecting plug and a second sealing gasket; a third mounting interface is arranged at the inner end of the attitude control nozzle section, and the third mounting interface is communicated with the second vent hole, the second connecting plug is threadedly connected with the third mounting interface, and the second sealing gasket is arranged between the second connecting plug and the second vent hole; The inner diameter of the orbit control plenum is greater than 2 times the throat diameter of the orbit control nozzle section; The internal passage diameter of the orbit control gas path is not less than 2 times the throat diameter of the orbit control nozzle section; The inner diameter of the attitude control plenum is greater than 2 times the throat diameter of the attitude control nozzle section; The internal passage diameter of the attitude control gas path is not less than 2 times the throat diameter of the attitude control nozzle section.

2. The model device for attitude-orbit control coupled jet interference force test according to claim 1, characterized in that, The outer diameter of the head portion gradually increases from the first end to the second end, and the outer diameter of the second end of the head portion is equal to the outer diameter of the orbit control nozzle section.

3. The model device for attitude-orbit control coupled jet interference force test according to claim 1, characterized in that, The end face of the second end of the attitude control nozzle section is provided with a second mounting cavity, the first end of the load cell is mounted in the second mounting cavity, and the first end of the load cell and the second end of the attitude control nozzle section are connected and fixed by a second pin.

4. The model device for attitude-orbit control coupled jet interference force test according to claim 3, characterized in that, A mounting boss is arranged between the attitude control plenum and the second mounting cavity, the mounting boss is provided with a fourth mounting interface, the fourth mounting interface is communicated with the attitude control plenum; the first end of the attitude control gas path is threadedly connected with the fourth mounting interface, and a second sealing ring is arranged between the attitude control gas path and the fourth mounting interface.

5. The model apparatus for attitude-orbit control coupled jet interference force test according to claim 1, characterized in that, The first end of the support rod is provided with a tapered hole, and the second end of the load cell is sealingly mounted in the tapered hole.

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