Pipeline integrated attitude control rocket engine thrust test structure and working method thereof

Abstract

The invention discloses a pipeline integrated attitude control rocket engine thrust test structure and a working method thereof, and belongs to the technical field of sensing measurement and control. The testing structure is composed of a front fixed frame, a rear fixed frame, a rear movable frame, a middle-layer movable frame, a front movable frame, a straight connecting beam, a front-end inclined connecting beam, a propellant supply pipeline, a rear-end inclined connecting beam, a sensitive beam, a thin film sensor and a supporting thin beam. The thrust generated by rocket eruption enables the engine and the adapter frame to displace, then a series of structures from the front movable frame to the rear movable frame are driven to move step by step in the horizontal direction, strain function film layers of the four film sensors on the sensitive beam are deformed, and finally a differential Wheatstone bridge is formed by the circuit board for testing. According to the invention, the film sensor and the propellant supply pipeline are integrated on the test structure, and the S-shaped propellant supply pipeline, the circular truncated cone type movable frame structure and the layered overall structure are designed, so that the sensitivity of the test sensor is remarkably improved while the high rigidity of the test device is ensured.

Description

Technical Field

[0001] The invention belongs to the technical field of sensing and control, and in particular relates to a test structure and a working method of the thrust of a pipeline-integrated attitude control rocket engine. Background Art

[0002] Space engines are the core power source of all spacecraft. Thrust testing is a key test indicator of space engine performance. Through thrust testing, it can provide a basic basis for the correction of space engine control strategy and the adjustment of assembly accuracy. Liquid attitude control rocket engines undertake tasks such as attitude adjustment, precise positioning, rapid maneuvering, rendezvous and docking, separation and braking. The accuracy of its thrust test will directly affect the flight control accuracy and target hit accuracy, so it is very necessary to conduct thrust testing.

[0003] In the thrust test of the attitude control rocket engine, one end of the propellant supply pipeline is directly connected to the engine, and the other end is fixed to the outside. The thrust generated during ignition causes the attitude control rocket engine to move. At this time, the propellant supply pipeline will constrain the displacement of the attitude control rocket engine, and its constraint will "consume" part of the thrust, resulting in the thrust measured in the laboratory not accurately reflecting the thrust of the attitude control rocket engine in the actual working process. In addition to the steady-state thrust test, the attitude control rocket engine also needs to be tested for dynamic thrust. The pulse ignition frequency of the attitude control rocket engine can reach 50Hz during operation. In order to ensure the accuracy of the lateral thrust, the thrust test device has weak local strength and will break under the action of high-frequency alternating loads, resulting in the inability to measure. At the same time, due to the complex structure of the propellant supply pipeline, the overall stiffness is poor and the stress state is unstable, under the action of high-frequency alternating loads, the thrust of the sensor test will be seriously distorted. The existing thrust test structure is often connected between the moving frame and the fixed frame, and between the moving frame and the propellant supply pipeline through connecting rods and threads. The overall structure has high requirements for assembly accuracy, and the error introduced by the assembly has a great impact on the measurement of small thrust. Therefore, it is necessary to study a new thrust test structure to greatly reduce the constraints of the propellant supply pipeline and improve the overall stiffness, reduce the impact of high-frequency alternating loads and assembly errors on thrust testing, and thus improve the accuracy of rocket engine thrust testing. Summary of the invention

[0004] The present invention provides a test structure for the thrust of a pipeline-integrated attitude control rocket engine and a working method thereof, which solve the problems of pipeline constraints, easy fracture at weak points, high assembly precision requirements and poor frequency response performance of the thrust test device described in the background technology.

[0005] In order to achieve the above object, the present invention adopts the following technical solution: In the first aspect, the present invention provides a test structure for the thrust of a pipeline-integrated attitude control rocket engine, including a thrust test frame and a thin film sensor, wherein the thrust test frame includes a propellant supply pipeline, a fixed frame structure and a moving frame structure located inside the fixed frame structure; the fixed frame structure includes a front fixed frame and a rear fixed frame fixedly connected; the moving frame structure includes a front moving frame, a middle moving frame and a rear moving frame fixedly connected in sequence; the two ends of the propellant supply pipeline are respectively fixedly connected to the front fixed frame and the front moving frame, and are connected to the pipeline through holes opened on the front fixed frame and the front moving frame; two sensitive beams are symmetrically distributed between the rear moving frame and the rear fixed frame, and the sensitive beams have two grooves, and thin film sensors are prepared on the top surfaces of the grooves.

[0006] Furthermore, the front moving frame, the middle moving frame and the rear moving frame are all circular ring structures, and the inner diameters and outer diameters of the three increase successively.

[0007] Furthermore, the front moving frame and the middle moving frame are fixedly connected via a plurality of front end oblique connecting beams, and the middle moving frame and the rear moving frame are fixedly connected via a plurality of rear end oblique connecting beams.

[0008] Furthermore, the thrust test frame is processed into an integrated structure by selective laser melting.

[0009] Furthermore, the propellant supply pipeline is an S-shaped pipeline.

[0010] Furthermore, the front fixed frame and the rear fixed frame are fixedly connected via a plurality of straight connecting beams, and two thin supporting beams are symmetrically connected between the straight connecting beams and the middle movable frame.

[0011] Furthermore, the sensitive beam is arranged in a vertical direction, and the angle between the sensitive beam and the supporting thin beam is 90°.

[0012] Furthermore, the pipeline through hole opened on the front moving frame is L-shaped, one end of the pipeline through hole is connected to the propellant supply pipeline, and the other end passes through the front end surface of the front moving frame.

[0013] Furthermore, the thin film sensor comprises an insulating layer, a strain wire grid is arranged on the insulating layer, and a protective layer and a metal electrode are arranged on the strain wire grid.

[0014] In a second aspect, the present invention provides a working method of a pipeline-integrated attitude control rocket engine thrust test structure, comprising: The fuel and oxidizer flow into the propellant supply pipeline through the external pipeline and the pipeline through-hole opened on the front fixed frame, then flow out from the front end surface of the front moving frame, and flow into the engine combustion chamber through another external pipeline; The fuel and oxidant are burned in the engine combustion chamber at different flow ratios; After combustion, the airflow ejected from the tail end of the engine generates reverse thrust, causing the engine and the adapter frame to shift, thereby driving the frame structure to move in the horizontal direction. The relative displacement between the rear moving frame and the rear fixed frame causes the connected sensitive beam to deform. In the four stress concentration areas of the two sensitive beams, the two places close to the rear moving frame are subjected to tensile stress in the vertical direction, while the two places far from the rear moving frame are subjected to compressive stress in the vertical direction. The stresses in different stress concentration areas cause the strain wire grids of the four thin film sensors prepared on the sensitive beams to deform accordingly, and the resistance value of the alloy wire grid in the strain wire grid changes accordingly. The flexible circuit board is pasted on the rear end surface of the sensitive beam, and four thin film sensors are connected in sequence to form a bridge through the circuit in the flexible circuit board. A DC voltage is applied between two relative nodes in the bridge. The tension resistor will form a high potential difference at both ends due to the increase in resistance, while the pressure resistor will form a low potential difference at both ends due to the decrease in resistance, thus forming a differential Wheatstone bridge; a voltmeter is connected between the other two relative nodes in the bridge circuit to record the output voltage; The thrust load generated by the attitude control rocket engine is calculated through the output voltage.

[0015] Compared with the prior art, the present invention has at least the following beneficial technical effects: The pipeline-integrated attitude control rocket engine thrust test structure provided by the present invention integrates the propellant supply pipeline and the test component into an integrated thrust test frame, simplifies the overall structure, and reduces the impact of assembly errors on the test; at the same time, when the engine ignites and generates displacement, the propellant supply pipeline can be displaced together with the dynamic frame, and the constraint of the propellant supply pipeline on the engine is transferred to the test frame, which greatly reduces the impact of the pipeline constraint on the thrust test. As the overall stiffness of the thrust test structure increases, its frequency response performance is improved, but its deformation will inevitably decrease, resulting in a decrease in sensor sensitivity. Therefore, the frequency response performance of the thrust test structure and its test sensitivity are two contradictory indicators.

[0016] The present invention designs an "S-shaped" structure for the propellant supply pipeline, which appropriately reduces its rigidity compared to the traditional "straight" pipeline, thereby increasing the deformation of the sensitive structure; by designing a three-layer dynamic frame, the propellant supply pipeline, the supporting thin beam and the sensitive beam are arranged in layers, compared with the same-layer arrangement, the deformation of the sensitive structure can be increased while ensuring the rigidity of the overall structure; by designing the three-layer dynamic frame as a truncated cone frame structure, the diameter of the dynamic frame is gradually increased from the front end to the rear end, and the displacement of the dynamic frame is amplified by using the connecting rod principle, while ensuring that the test structure has a high rigidity, the test sensitivity is significantly increased.

[0017] Furthermore, the test sensor is integrated on the surface of the sensitive beam using a thin film preparation process, eliminating the need for external sensors. The overall structure is simple and compact, which not only reduces the loss in the stress transfer process of traditional adhesive strain gauges, but also reduces the weight of the entire test structure, improving the stiffness of the test structure and its ability to resist high-frequency alternating loads. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 Three-dimensional thrust test structure for pipeline-integrated attitude control rocket engine Figure 1 ; Figure 2 Three-dimensional thrust test structure for pipeline-integrated attitude control rocket engine Figure 2 ; Figure 3 It is a cross-sectional view of the front fixed frame, front moving frame and propellant supply pipeline; Figure 4 This is the cross-sectional view of the “L-shaped” pipeline through hole of the front moving frame; Figure 5 It is a cross-sectional view of the propellant supply pipeline; Figure 6 It is a three-dimensional diagram of the sensitive beam structure; Figure 7 It is the cross-sectional view of the sensitive beam groove structure; Figure 8 This is a cross-sectional view of the thrust test structure of the pipeline-integrated attitude control rocket engine; Fig. 9 Schematic diagram of the thin film sensor structure.

[0019] In the attached figure, 1, front fixed frame; 2, rear fixed frame; 3, rear moving frame; 4, middle moving frame; 5, front moving frame; 6, straight connecting beam; 7, front oblique connecting beam; 8, propellant supply pipeline; 9, rear oblique connecting beam; 10, sensitive beam; 11, thin film sensor; 12, supporting thin beam; 13, SiO 2 Insulating layer; 14, strain wire grid; 15, protective layer; 16, metal electrode. DETAILED DESCRIPTION

[0020] The present invention is described in detail below with reference to the accompanying drawings and specific embodiments.

[0021] In order to enable those skilled in the art to better understand the technical solutions in the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work should fall within the scope of protection of the present invention.

[0022] It should be noted that when an element is referred to as being "disposed on" another element, it may be directly on the other element or there may be another element centered thereon. When an element is considered to be "connected to" another element, it may be directly connected to the other element or there may be another element centered thereon at the same time. The terms "upper", "lower", "front", "back", "left", "right", "top", "bottom", "inside", "outside", etc. used herein indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0023] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as those generally understood by those skilled in the art of the present invention. The terms used herein in the specification of the present invention are only for the purpose of describing specific embodiments and are not intended to limit the present invention. The term "and / or" used herein includes any and all combinations of one or more related listed items.

[0024] Example 1 Reference Figures 1 to 8 The present embodiment provides a test structure for the thrust of a pipeline-integrated attitude control rocket engine, which includes an integrated thrust test frame consisting of a front fixed frame 1, a rear fixed frame 2, a front moving frame 5, a middle moving frame 4, a rear moving frame 3, eight straight connecting beams 6, six front end oblique connecting beams 7, a propellant supply pipeline 8, six rear end oblique connecting beams 9, two sensitive beams 10 and two supporting thin beams 12, and four thin film sensors 11.

[0025] The front moving frame 5 , the middle moving frame 4 and the rear moving frame 3 form a three-layer moving frame, and the three-layer moving frame is located inside the front fixed frame 1 and the rear fixed frame 2 .

[0026] The front fixed frame 1 and the rear fixed frame 2 are both annular bosses, each of which is provided with eight identical circular bolt holes. When testing, bolts are passed through the bolt holes to connect with the test bench. The front end surfaces of the front fixed frame 1 and the front moving frame 5 are located in the same plane.

[0027] The center of the circle of the front fixed frame 1 and the rear fixed frame 2 is kept in a straight line, and the front fixed frame 1 and the rear fixed frame 2 are connected by eight straight connecting beams 6, which are perpendicular to the front fixed frame 1 and the rear fixed frame 2 to ensure that the thrust test frame has sufficient rigidity; the front moving frame 5 and the rear moving frame 3 are both circular ring structures, and the middle moving frame 4 is a circular truncated cone structure. The center of the circle of the three-layer moving frame is kept in a straight line, and the inner diameter and outer diameter of the ring gradually increase from front to back, and the ratio of the outer diameter of the last level of the ring to the outer diameter of the first level of the ring is more than 1.5 times. The front moving frame 5 and the middle moving frame 4 are fixedly connected by six front end oblique connecting beams 7, and the middle moving frame 4 and the rear moving frame 3 are fixedly connected by six rear end oblique connecting beams 9. The six front end oblique connecting beams 7 and the six rear end oblique connecting beams 9 are arranged on the same six inclined planes, and the overall structure of the three-layer moving frame is a truncated cone frame structure.

[0028] Two "L-shaped" frame pipeline through holes are processed on the front frame 5. One end of the frame pipeline through hole is connected to the propellant supply pipeline 8, and the other end passes through the front end surface of the front frame 5. An adapter is welded at the frame pipeline through hole on the front end surface and the pipeline is connected to the combustion chamber of the attitude control rocket engine. At the same time, four circular bolt through holes are distributed on the front frame 5. The second bolt through hole is used to connect with the adapter frame and the attitude control rocket engine through bolts.

[0029] Two "S-shaped" propellant supply pipelines 8 are designed between the front fixed frame 1 and the front moving frame 5. The cross-section of the propellant supply pipeline 8 is a rectangular structure on the outside and a circular through hole with a diameter of 6 mm on the inside. Two square bosses are symmetrically distributed in the horizontal direction on the outer wall of the front fixed frame 1. The center of the boss is a circular boss pipeline through hole. The boss pipeline through hole runs through the side wall of the front fixed frame 1 and is connected to the "S-shaped" propellant supply pipeline 8. An adapter is welded at the boss pipeline through hole to connect to the external pipeline, and is connected to the external fuel and oxidant supply ends respectively. Semicircular bosses are distributed on the outer wall of the front fixed frame 1 at a 45° angle with the horizontal direction. The four semicircular bosses are used to cooperate with the clamp during grinding.

[0030] Two thin supporting beams 12 are symmetrically connected between the middle-layer moving frame 4 and the straight connecting beam 6. The thin supporting beams 12 are arranged in the middle of the middle-layer moving frame 4 in a horizontal direction.

[0031] There are two rectangular sensitive beams 10 symmetrically distributed between the rear moving frame 3 and the rear fixed frame 2. The sensitive beams 10 are arranged in a vertical direction, and the angle between them and the supporting thin beams 12 is 90°. The rear end surfaces of the sensitive beams 10, the rear moving frame 3 and the rear fixed frame 2 are in the same plane. Two rectangular grooves are processed on each sensitive beam 10 to form a stress concentration area, and a thin film sensor 11 is prepared on the stress concentration area. The flexible circuit board is pasted on the rear end surface of the sensitive beam 10, and the electrodes on it are connected to the metal electrodes 16 of the four thin film sensors 11 by gold wire bonding. Finally, the circuit in the flexible circuit board connects the four thin film sensors 11 in sequence to form an electric bridge.

[0032] Reference Fig. 9 The thin film sensor 11 includes SiO 2 Insulating layer 13, SiO 2 A strain wire grid 14 is disposed on the insulating layer 13 , and a protective layer 15 and a metal electrode 16 are disposed on the strain wire grid 14 .

[0033] Six circular bolt through holes are evenly distributed on the rear moving frame 3, and the thrust test structure is connected to the thrust calibration device through the bolt through holes and bolts, which is used for thrust calibration and correction of the thrust test frame.

[0034] Example 2 Reference Fig. 9 , this embodiment provides a method for preparing a thin film sensor as follows: Step 1: Surface treatment of the sensitive beam: The rear end surface of the sensitive beam 10 is processed by rough grinding, fine grinding and polishing to ensure that the surface roughness after polishing is less than 20nm and there are no micron-level pits and scratches.

[0035] Step 2: Preparation of insulating layer: A 2-3 μm thick SiO2 layer is prepared on the rear end surface of the stress concentration area of ​​the sensitive beam 10 by magnetron sputtering process. 2 Insulating layer 13.

[0036] Step 3: Preparation of strain functional film layer. A wire grid pattern mask layer is prepared on the composite flexible film using a femtosecond laser. After the preparation is completed, the flexible mask is transferred to the stress concentration area and a magnetron sputtering process is used to deposit the strain functional film layer on the SiO 2 A Karma alloy film with a thickness of 200-300 nm is deposited on the surface of the insulating layer 13, and the mask is finally peeled off to obtain a strain wire grid 14 with a target pattern structure.

[0037] Step 4: Preparation of electrodes and protective layer. Using flexible mask technology and magnetron sputtering process, metal electrodes 16 and SiO 2After the preparation is completed, the flexible circuit board is pasted on the rear end surface of the sensitive beam 10, and the metal electrode 16 is connected to the gold electrode of the flexible circuit board by gold wire bonding technology. Finally, the circuit in the flexible circuit board connects the four thin film sensors 11 in sequence to form a differential Wheatstone bridge for signal output.

[0038] Example 3 The working process of the test structure of the pipeline integrated attitude control rocket engine thrust described in Example 1 provided in this embodiment is as follows: The external fuel supply end and the oxidant supply end respectively pass the fuel and the oxidant through the external pipeline and the adapter at the side end of the front frame 1, and flow from the front frame 1 into the propellant supply pipeline 8, and then flow out from the front end surface of the front moving frame 5, flow through the adapter and another external pipeline, and finally flow into the engine combustion chamber; The fuel and the oxidant burn in the engine combustion chamber at different flow ratios. After combustion, the airflow ejected from the tail end of the engine generates reverse thrust, causing the engine and the adapter to shift, thereby driving the front moving frame 5, the six front oblique connecting beams 7, the middle moving frame 4, the six rear oblique connecting beams 9 and the rear moving frame 3 to gradually move in the horizontal direction. The relative displacement between the rear moving frame 3 and the rear fixed frame 2 will cause the connected sensitive beam 10 to deform. Among the four stress concentration areas of the two sensitive beams 10, the two places close to the rear moving frame 3 are subjected to tensile stress in the vertical direction, while the two places far from the rear moving frame are subjected to compressive stress in the vertical direction; the stresses in different stress concentration areas will cause the strain wire grids 14 of the four thin film sensors 11 prepared thereon to deform accordingly, and the resistance value of the strain wire grids 14 will change accordingly, wherein the resistance value of the strain wire grids increased, and the resistance value of the strain wire grids decreased. Four thin film sensors 11 are connected in sequence to form a bridge through a flexible circuit board pasted on the rear end surface of the sensitive beam 10 according to the principle of "adjacent arms are opposite and opposite arms are the same". A 5V DC voltage is passed between two relative nodes in the bridge. The tension resistor will form a high potential difference at both ends due to the increase in resistance, while the pressure resistor will form a low potential difference at both ends due to the decrease in resistance, thus forming a differential Wheatstone bridge. A voltmeter is connected between the other two relative nodes in the bridge circuit to record the output voltage. Before the test, a linear correspondence is established between the output voltage and the thrust load through the standard mechanical sensor on the thrust calibration device. In the final test, the thrust load generated by the attitude control rocket engine is obtained by recording the output voltage.

[0039] The term "consisting of" describing a combination shall include the identified elements, ingredients, parts or steps and other elements, ingredients, parts or steps that do not substantially affect the basic novel characteristics of the combination. The use of the terms "comprising" or "including" to describe a combination of elements, ingredients, parts or steps herein also contemplates embodiments that consist essentially of these elements, ingredients, parts or steps. By using the term "may", it is intended to illustrate that any of the attributes described that "may" be included are optional.

[0040] Multiple elements, ingredients, parts or steps can be provided by a single integrated element, ingredient, part or step. Alternatively, a single integrated element, ingredient, part or step can be divided into separate multiple elements, ingredients, parts or steps. The disclosure "one" or "an" used to describe an element, ingredient, part or step is not intended to exclude other elements, ingredients, parts or steps.

[0041] It should be understood that the above description is for illustration and not for limitation. Many embodiments and many applications beyond the examples provided will be apparent to those skilled in the art upon reading the above description. Therefore, the scope of the present teachings should not be determined with reference to the above description, but rather with reference to the foregoing claims and the full scope of equivalents to which such claims are entitled. For the purpose of comprehensiveness, all articles and references, including disclosures of patent applications and publications, are incorporated herein by reference. The omission of any aspect of the subject matter disclosed herein in the foregoing claims is not intended to be a waiver of such subject matter, nor should it be considered that the applicant has not considered such subject matter to be part of the disclosed inventive subject matter.

Claims

1. A test structure for the thrust of a pipeline-integrated attitude control rocket engine, characterized in that: The thrust test frame comprises a thrust test frame and a thin film sensor (11), wherein the thrust test frame comprises a propellant supply pipeline (8), a fixed frame structure and a movable frame structure located inside the fixed frame structure; the fixed frame structure comprises a front fixed frame (1) and a rear fixed frame (2) which are fixedly connected; the movable frame structure comprises a front movable frame (5), a middle movable frame (4) and a rear movable frame (3) which are fixedly connected in sequence; The two ends of the propellant supply pipeline (8) are respectively fixedly connected to the front fixed frame (1) and the front moving frame (5), and are communicated with pipeline through holes provided on the front fixed frame (1) and the front moving frame (5); Two sensitive beams (10) are symmetrically distributed between the rear moving frame (3) and the rear fixed frame (2), the sensitive beams (10) having two grooves, and thin film sensors (11) are prepared on the top surfaces of the grooves.

2. The test structure for thrust of a pipeline-integrated attitude control rocket engine according to claim 1, characterized in that: The front moving frame (5), the middle moving frame (4) and the rear moving frame (3) are all annular structures, and the inner diameters and outer diameters of the three increase successively.

3. The test structure for thrust of a pipeline-integrated attitude control rocket engine according to claim 1, characterized in that: The front moving frame (5) and the middle moving frame (4) are fixedly connected via a plurality of front end oblique connecting beams (7), and the middle layer moving frame (4) and the rear moving frame (3) are fixedly connected via a plurality of rear end oblique connecting beams (9).

4. The test structure for thrust of a pipeline-integrated attitude control rocket engine according to claim 1, characterized in that: The thrust test frame is processed into an integrated structure by selective laser melting.

5. The test structure for thrust of a pipeline-integrated attitude control rocket engine according to claim 1, characterized in that: The propellant supply pipeline (8) is an S-shaped pipeline.

6. The test structure for thrust of a pipeline-integrated attitude control rocket engine according to claim 1, characterized in that: The front fixed frame (1) and the rear fixed frame (2) are fixedly connected via a plurality of straight connecting beams (6), and two thin supporting beams (12) are symmetrically connected between the straight connecting beams (6) and the middle layer moving frame (4).

7. The test structure for thrust of a pipeline-integrated attitude control rocket engine according to claim 6, characterized in that: The sensitive beam (10) is arranged in a vertical direction, and the angle between it and the supporting thin beam (12) is 90°.

8. The test structure for thrust of a pipeline-integrated attitude control rocket engine according to claim 1, characterized in that: The pipeline through hole formed on the front moving frame (5) is L-shaped, one end of the pipeline through hole is connected to the propellant supply pipeline (8), and the other end passes through the front end surface of the front moving frame (5).

9. The test structure for thrust of a pipeline-integrated attitude control rocket engine according to claim 1, characterized in that: The thin film sensor (11) comprises an insulating layer, a strain wire grid (14) is arranged on the insulating layer (13), and a protective layer (15) and a metal electrode (16) are arranged on the strain wire grid (14).

10. The working method of the test structure of the pipeline-integrated attitude control rocket engine thrust according to any one of claims 1 to 9, characterized in that: include: The fuel and the oxidizer flow into the propellant supply pipeline (8) through the external pipeline and the pipeline through-hole opened on the front fixed frame (1), then flow out from the front end surface of the front moving frame (5), and flow into the engine combustion chamber through another external pipeline; The fuel and oxidant are burned in the engine combustion chamber at different flow ratios; After combustion, the airflow ejected from the rear end of the engine generates reverse thrust, causing the engine and the adapter frame to shift, thereby driving the frame structure to move in the horizontal direction. The relative displacement between the rear moving frame (3) and the rear fixed frame (2) causes the connected sensitive beam (10) to deform. In the four stress concentration areas of the two sensitive beams (10), two locations close to the rear moving frame (3) are subjected to tensile stress in the vertical direction, while two locations away from the rear moving frame (3) are subjected to compressive stress in the vertical direction. The stresses in different stress concentration areas cause the strain wire grids (14) of the four thin film sensors (11) prepared on the sensitive beams (10) to deform accordingly, and the resistance value of the alloy wire grid in the strain wire grid (14) changes accordingly. A flexible circuit board is pasted on the rear end surface of the sensitive beam (10), and four thin film sensors (11) are connected in sequence through the circuit in the flexible circuit board to form an electric bridge. A DC voltage is applied between two relative nodes in the electric bridge, and a high potential difference is formed at both ends of the tension resistor due to the increase in resistance, while a low potential difference is formed at both ends of the pressure resistor due to the decrease in resistance, thereby forming a differential Wheatstone bridge; a voltmeter is connected between the other two relative nodes in the bridge circuit to record the output voltage; The thrust load generated by the attitude control rocket engine is calculated through the output voltage.

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