Aerospace craft track-controlled engine control method based on impulse equivalence principle
An impulse equivalent principle and aerospace vehicle technology, applied to the power supply system of aerospace vehicles, etc., can solve the problems of the engine not being able to effectively track commands, control performance degradation, and reduced precision, so as to reduce errors, improve accuracy, and improve guidance. The effect of precision
- Summary
- Abstract
- Description
- Claims
- Application Information
AI Technical Summary
Problems solved by technology
Method used
Image
Examples
specific Embodiment approach 1
[0028] According to the control method of the aerospace vehicle orbit control engine based on the impulse equivalent principle in this embodiment, the No. 1 engine, the No. 2 engine, the No. 3 engine and the No. 4 engine are evenly installed around the center of mass of the missile, and the installation positions are as follows: figure 1 As shown, the control method is realized through the following steps:
[0029] Step 1. Decompose the aerospace vehicle into two planes along the body coordinate system, the longitudinal plane and the lateral plane, the longitudinal plane is controlled by the No. 1 engine and the No. 3 engine, and the lateral plane is controlled by the No. 2 engine and number four engine control;
[0030] Step 2. First, define the possible equivalent force extreme value situation of each engine in the No. 1 engine, No. 2 engine, No. 3 engine and No. 4 engine: divide the control process of the engine into Steady off state and the engine is in a steady on state ...
specific Embodiment approach 2
[0042] Different from Embodiment 1, the thrust waveform generated by the engine is not a strict rectangle in the actual dynamic characteristic diagram of the aerospace vehicle orbital engine control method based on the impulse equivalent principle in this embodiment, such as figure 2 The delay time shown exists with t d Indicates that the rise time is t r Indicates that the falling time is t f Indicates that the engine control period is t c Indicates that when the engine reaches a stable start, the thrust is F s Indicates that the force required for the guidance command is F c express;
[0043] Minimum closing equivalent force as stated in step 2 The calculation process of is specifically as follows: According to the principle of equivalent impulse, that is F off min t c = 1 2 t r F ...
specific Embodiment approach 3
[0047] Different from the specific embodiment 1 or 2, in the control method of the aerospace vehicle orbital engine based on the impulse equivalent principle of this embodiment, in step 3,
[0048] The engine on time T on The acquisition process is: when the engine is off at the beginning of the current control cycle, the engine may be turned on, so it is necessary to determine the engine on time T on ; When the engine is on at the beginning of the current control cycle, the engine does not need to be turned on again, and there is no engine on time T at this time on value;
[0049] At the same time, define the stable state of the engine at the beginning of the control cycle as BeginStatus, define the stable state of the engine at the end of the control cycle as EndStatus, and combine the stable state of the engine at the beginning of the control cycle BeginStatus and the engine's The value of the steady state EndStatus reached at the end of the control cycle is defined as tw...
PUM
Login to View More Abstract
Description
Claims
Application Information
Login to View More